THE WORLD OF TOMORROW New Concepts, Ideas, Innovations in Aerospace, Technology and the Human Sciences
New Concepts, Ideas, Innovations
in Aerospace, Technology
and the Human Sciences
Alexander Bolonkin
Dr.Sci., Professor of Russian and American Universities
Former Senior Researcher of NASA
USA Air Force and Russian Space Industry
NOVA
2 Alexander Bolonkin
Content
Abstract
Preface
Part A.
New concepts and ideas in aerospace
1. AB Levitation and Electricity Storage
2. Electrostatic AB Ramjet Space Propulsion
3. Beam Space Propulsion
4. Space Magnetic Sail: Some Common Mistakes; and the Electrostatic Magsail
5. The High Speed Solar Sail
6. Transfer of Electricity into Outer Space
7. Thermonuclear Propulsion
8. New Method of Atmospheric Reentry
9. Solid Space Tower
10. Electrostatic Linear Engine and Cable Space Launcher
11. Optimal Electrostatic Space Tower (Mast, New Space Elevator)
12. AB Levitrons and their Applications to Earth‘s Motionless Satellites
Part B
New ideas in technology
1. Micro (Mini) - Thermonuclear Reactor
2. Utilization of Wind Energy at High Altitude
3. Control of Regional and Global Earth weather
4. Conversion of Deserts and Polar Earth Regions into Gardens
5. Cheap Textile Dam Protection of Seaport Cities against Hurricane Storm Surge
Waves, Tsunamis, and Other Weather-Related Floods
6. A Low-Cost Natural Gas/Freshwater Aerial Pipeline
7. Air Observation System
8. Extraction of Freshwater and Energy from the Atmosphere
Part C
New ideas in human science
Electronic society and electronic immortality
1.The Twenty - First Century: The advent of the non-biological civilization
2.Twenty - First Century - the beginning of human immortality.
3. Science, soul, paradise, and artificial intelligence
4. Breakthrough to immortality.
Summary
Appendix
1. Space Research: Organizing For Economy and Efficiency
2. System of Units and Other Useful Values
General References
Index
New Concepts, Ideas and Innovations in Aerospace… 3
ABSTRACT
In last years the author and other scientists have published a lot of new concepts,
ideas, and innovations in aerospace, science, and technology. These ideas promise the
revolutions in aerospace, technology and human life.
In aerospace these include the new method of flight - AB levitation. This method
allows humanity to flight as bird, riches a very high speeds and free flight to space; the
electrostatic ramjet and beam space propulsions; electrostatic magsail; high speed solar
sail; a transfer of electricity in long distance at space; the space thermonuclear
propulsion, the new electrostatic engine which can be used as driver for space launcher
and accelerator of space ships, as an engine in new electrostatic high speed train; etc.
In technology these include the new mini-thermonuclear reactor, utilization of high
altitude wind energy, protection from tsunami, control of local and global weather,
converting of deserts and polar Earth regions in 'evergreen' gardens, high altitude gas
pipeline, and so on.
In human science there include electronic immortality of people.
New ideas in space/aviation may be useful for flights in space and in planet
atmosphere. Some of these have the potential to decrease launch costs thousands of
times, other allow the speed and direction of space apparatus to be changed without the
spending of fuel.
The author summarizes some revolutionary concepts, ideas, innovations, and
methods for scientists, engineers, students, and the public. He seeks attention from the
public, engineers, inventors, scientists for these innovations and he hopes the media,
government and the large aerospace companies will increase research and development
activity in these areas.
New Concepts, Ideas and Innovations in Aerospace…
PREFACE
The new concepts, ideas, methods, and innovation are only considered. There are a lot of
problems that must be researched, modeled, and tested before these ideas can be developed,
designed, built, and utilized. In offered book we describe some of them in aerospace,
technology, and humanity. Most of ideas are described in the following way: 1) there is a
brief explanation of the idea including its advantages and short comings; 2) then methods
estimation and computations of the main system parameters, and 3) a brief description of
projects, including estimations of the main parameters.
The first and third parts are in a popular form accessible to the wider public, the second
part is requires some mathematical and scientific knowledge of technical graduate students.
The book gives the main physical data and technical equations in attachment which will help
researchers, engineers, students and readers make estimations for their projects. Also
inventors will find the extensive field an inventions and innovations in this book.
The author has published a lot of new ideas and articles and macroprojects about
aerospace, technology, and human future in recent years (see General References at the end of
the book). That is, the way he seeks to draw more attention to new ideas than the old ideas
that are covered in many publications and are well-known to scientist and the public.
The book mainly contains material from the author‘s articles published in the last few
years.
New Concepts, Ideas and Innovations in Aerospace…
PART A. NEW CONCEPTS AND IDEAS IN AEROSPACE
Chapter 1
AB LEVITATOR AND ELECTRICITY STORAGE
ABSTRACT
The author researched this new idea – support of flight by any aerial vehicles at
significant altitude solely by the magnetic field of the planet. It is shown that current
technology allows humans to create a light propulsion (AB engine) which does not
depend on air, water or ground terrain. Simultaniosly, this revolutionary thruster is a
device for the storage of electricity which is extracted and is replenished (during braking)
from/into the storage with 100% efficiency. The relative weight ratio of this engine is
0.01 - 0.1 (from thrust). For some types of AB engine (toroidal form) the thrust easily
may be changed in any direction without turning of engine.
The author computed many projects using different versions of offered AB engine:
small device for levitation-flight of a human (including flight from Earth to Outer Space),
fly VTOL car (track), big VTOL aircrat, suspended low altitude stationary satellite,
powerful Space Shuttle-like booster for travel to the Moon and Mars without spending
energy (spended energy is replenished in braking when ship returns from other planet to
its point of origin), using AB-devices in military, in sea-going ships (submarimes), in
energy industry (for example. as small storage of electric energy) and so on. The vehicles
equipped with AB propulsion can take flight for days and cover distances of tens
thousands of kilometers at hypersonic or extra-atmosphere space speeds.
The work contains tens of inventions and innovations which solves problems and
breaks limitations which appear in solution of these very complex revolutionary ideas.
Keyword: AB levitator, levitation, non-rocket outer space flight, electric energy storage,
AB propulsion, AB engine, Bolonkin.
Published in http://arxiv.org on ruary 28, 2007 (search ―Bolonkin‖).
8 Alexander Bolonkin
1.INTRODUCTION
Free flight in the atmosphere as by birds was the ancient dream of people without aircraft.
During 1964, the author developed his first gravity control theory [1]. The first realistic
method for electrostatic levitation was offered and theoretically developed in report [2] and
published in [3] Ch.15.
However, the electrostatic levitation is possible only along special electrostatic lines.
Man (car, track) cannot fly in any direction and to any place in the Earth. Riding a vehicle
with air engine (propeller or rocket) for thrust, such persons cannot even imagine or feel
himself as being like a bird.
The offered new revolutionary method does not have these defects. It allows flight in any
direction in Earth's using the internal electricity storage. It does not depend on the
environment of air, water, ground and does not pollute regions or the planet in any way. It can
operate in vacuum, in the outer space surrounding any planet (space body) having a natural or
artificial magnetic field. The momentum ratio of magnet dipoles the Jupiter, Saturn, Earth,
Mercury, Mars are 20,000, 500, 1, 3/5000, 3/10,000 respectively. Mars‘ moon Phobos,
Magnetic Stars, White Dwarf also have the magnetic field up B = 80,000 T. The neutron stars
Magnetar have the magnetic field up 1011 T.
That can change the thrust direction without turning of the engine, levitate without
expending energy. That spends energy only for lifting and to overcome air drag, but lifting
energy is returning when the apparatus descends. We do not lose energy if we flight in space
or at planet not having an atmosphere and return to the initial take-off place. We can free
flight to Moon or Mars without loss of the summary energy from a Low Earth's Orbit if a
space apparatus has a same weight. Energy spended for the acceleration of apparatus will be
returned when apparatus is braking.
This work contains conventional sections: 1. The short description of the offered AB
levitator (that also may be used as friendly environmental electric car and other vihicle
engine), its works; 2) Theory of innovation, and 3) Projects estimations. The first and third
expositive sections are destined for non-specialist readers, the second part - for specialists.
2. BRIEF DESCRIPTION OF NEW REVOLUTIONARY
INNOVENTION
The offered method embraces tens inventions and innovations: magnetic devices,
superconductivity devices, electricity storage, compensation of magnetic forces, use of strong
matters, defence from magnetic field, concentration of magnetic field, increasing of magnetic
intensity, cooling systems, in protection from space radiation, special design of magnetic and
cooling devices, and many others. Some of them are briefly described below.
1. Note from theory. It is well-known from physics when the conductor is moved in
magnetic field that has an electromagnetic force and voltage between its ends. This force is
computed by equation:
dF i[dlB],
(1)
New Concepts, Ideas and Innovations in Aerospace… 9
where small vector
dF
is force (in Newtons) of small element
dl
of vector wire (in meters);
B
is intensity of the magnetic field, in Teslas; i is electric currency, in Ampers. Square
brackets [ ] note a vector production.
For straight wire the equation (1) can be written in form
[ ], or sin( , ), or ,
n
F i lB F ilB l B F ilB
(2)
where F is force, N; i is electric currency, A; l is wire length, m; B is magnetic field strength,
T; Bn is projection vector
B
on perpendicular to plate contains the vectors
l , B
. The
direction of force may be found by left hand rule: if magnetic lines enter into the human
hand‘s palm, the fingers show the direction of electric currency, then the pollex shows the
direction of magnetic force.
The electric tension (voltage), U, is computed by equations
n U lvB ,
(3)
where v is wire speed, m/s.
The force acts to the conductor and does not depend on wire speed. That explains why
our devices can levite without movement.
The equations (1)-(2) allow easy computation of the force and voltage of conductor in
magnetic field. However, if we estimate the force in Earth's magnetic field, this force is very
small. The Earth's magnetic field strength in a middle latitude equals about B 3.410-5
T. If
the conductor has the currency i = 10 A and length l = 1 m, the force will be only F =
3.410-4 N. That very small force is enough for moving a compass needle, but not enough for
moving a larger apparatus or for flight apparatus.
2. Design and work of AB levitator, engine and electric storage. Author offers to
overcome this difficulty by use of superconductivity, which allows a big currency up 105
A/mm2
and more. That means that one meter from superconductivity wire having crosssection
area 3 cm2
and mass 4.8 kg can create a force of about 2000 N. But superconductivity
calls to mind two other main problems: the low temperature of superconductivity and a
limited maximum self-magnetic field that destroys the wire‘s superconductibity.
These new problems we will consider later. Now, we consider the main principal
difficulty: the Maxwell law says: in any closed loop electric circuit (without internal
conductor) the total force (and electric intensity for constant magnetic flow) equals zero. That
means the back conductor (Figure 1a) creates the same opposed force F and total force will be
zero. The author offers the innovation which permits avoidance of this obstacle: to protect a
back wire from Earth's magnetic field (Figure 1b). It is known, an iron (or other good
magnetic) cover adsorbs the magnetic lines (Figure 1c) (see textbook "Electricity" by S.G.
Kalashnikov, 1985, p. 219, Figure 167, Russian). The back wire inserted into the iron cover
and insulated from it (Figure 1b).
That idea is used for AB thruster and AB levitator (Figure2). The author offers two main
forms of these devices: cylindrical form (long or shirt cylinder) and toroidal form. Naturally,
each of them has advantages and disadvantages. The cylindrical form is shown in Figure 2.
10 Alexander Bolonkin
Notations: 1 - closed loop wire, 2 - electric insulator, 3 - protection (shield) from outer magnetic field
(for example, iron, paramagnetic, ferromagnetic, etc.), 4 - lines of magnetic field, F - force, i -
electric currency, B - magnetic field strength.
Figure 1. Explanation of design and work the conventional closed loop electric circuit into a magnetic
field and offered AB device that creates force in the magnetic field. (a) Conventional electric circuit
in the magnetic field. We have two opposed magnetic force F. (b) Electric circuit which has the back
conductor protected from Earth's magnetic field. We have one force. (c) Magnetic lines flow around
the back conductor. Direct exposure shield protects the back electric wire from Earth's magnetic field
(cross-section of back wire 3 in "c").
The cylindrical AB thruster has closed loop superconductivity wires 4-6 (Figure 2)
inserted into strong composed insulator 5 (that stuff is composed from strong fibers or
whiskers). That is also important innovation because insulator perceives the gigantic magnetic
tensile forces from superconductive wires. The safety force very strong depends from this
insulator. The insulator is also stores the electric energy. The amount of stored energy
depends from an insulator‘s strength. Strong artificial fibers, whiskers, and nanotubes are
preferable as the insulator (stuff). The known (for example, toroidal) superconductor electric
storage has empty core. That needs in a strong heavy cover and cannot have a strong internal
magnetic field. The design offered connects the straight and back wires 4, 6 in one body by
the insulator and allows reaching a very strong magnetic field between wires 4 and 6 (see
computation). The strong insulator also supports the superconductivity wire 4, 6 because
superconductivity material has usually a small strength. The superconductive layer 11 is
connected with wires 4. It is known that external magnetic field cannot penetrate the
New Concepts, Ideas and Innovations in Aerospace… 11
superconductive material more than 10-5
cm. The layer 11 accepts the Earth's magnetic field,
passes voltage to the upper wire 4 and protects the top side of the lower back wire 6 from
influence the Earth's magnetic field. The face plates 7 (or special internal cylinder made from
thin ferro-magnetic (iron) material) also protects the internal side of the back wires 7 from
Earth's magnetic field.
Figure 2. Cylindrical superconductivity AB engine for levitator, mobile and flight apparatus and
vehicles. (a) Side view cross-section; (b) Forward view; (c) Cross-section of forward view.
Notations: 1 - cover, 2 - heat high efficiency protection (multi- high efficiency screen-mirrors); 3 -
channels of the cooling system (for example by liquid nitrogen), 4 - superconductive wires inserted
into the strong light insulator, 5 - strong composite insulator, 6 - back conductor, 7 - side protection
from Earth's magnetic field, 8 - charge and discharge device, 9 - pump for liquid refrigerant, 10 -
mobile protections of device parts from Earth's magnetic field (for control value and direction of the
levitation (thrust) force), 11 - superconductive thin layer connected to wires 4. That protects the wires
6 from Earth's magnetic field.
The cylindrical levitator may be short (Figure2‘) or has a thin envelope. This form is
more suitable for air vehicles.
Figure 2’. Short cylindrical AB levitator and superconductive ring-storage of electric energy. (a)
General view, (b) Cross-section of ring.
12 Alexander Bolonkin
The levitator has channels 4 where the liquid refrigerant (for example, nitrogen)
circulates by a pump 9. The levitator has an innovative heat protection: multi-screens vacuum
prism mirror offered by author in [3] Chs.3A, 12. The loss of refrigerant by leakage is small
(see computation) and unimportant to operation. In outer space the levitator is protected from
Sun and Earth radiations by the same multi-screens protector and does not need liquid
refrigerant and special cooling system.
The mobile sections 10 (from thin iron (ferro-magnetic), circle and semi-circle) allows
defense of part of the outer cylindrical surface from Earth's magnetic field and change (move)
position and value of levitation force. The charging and discharging of the electricity storage
feature (insulator between wires 4 - 6) makes inductor 8 or special outer magnetic field. We
do not spend energy when the levitator levitates or moves in horizontal direction. The energy
in storage is automatically spent (or replenished) when apparatus is lifting (descent), is
accelerated (braking), or having movement drag (air and friction drag). That way we can free
(without spending of total energy) travel in space or non-atmospheric planet if we will return
at previous place and doesn't change the final weight. That capability doesn't have any known
engines. The efficiency of offered electricity storage is 100% and energy saved for an
unlimited time period.
The AB levitetor can have a toroidal form (Figure 3). This form may be better for plate
flight vehicles.
3. Control of AB levitator. The guidence and control of the levitating apparatis is easily
accomplished. The control of the levitation force (value and direction) is presented in Figure
4. We can slope the levitative force F in any direction, to get a projection of this force to
horizotal plate and move in any horizontal direction (without turning of apparatus!).
Expecially that is comfortable for toroidal levitator (Figure 4h). We can also turn the
apparatus around any axis. Our apparatus is neutral, but one can be stabilized quickly by the
simplest gyroscopical device.
Our apparatus may be used for ground, sea ship, submarine vehicles as engine (thruster)
and storage of electric energy.
Figure 3. Toroidal form of AB levitator. (a) Top view, (b) Side view, (c) Cross-section. Notations: 1 -
toroidal levitator and electric storige, 3 - envelope, 4- heat protection, 5 - refrigerent, 6 -
superconductive wires, 7 - strong material, 8 - protection from Earth's magnetic field and mobile
control of value and direction of levitate force.
New Concepts, Ideas and Innovations in Aerospace… 13
Figure 4. Control of value and direction of the levitation force. (a) Axis of cylindrical levitator. (b) The
closing of part cylinder from Earth's magnetic fields (left end) moves the levitate force F from the
center of gravity and creates the moment around axis y. (c) The slope of cylinder bends the force F and
creates the horizontal force. (d) The closing of part cylinder from Earth's magnetic field moves the F
from the center of gravity and creates the moment around axis x. (e) The different forces F of two
connected cylinder create the moment around axis x. (f) Ferromagnetic antenns returns the Earth's
magnetic field near levitator and produce force when the levitator moves along the lines of Earth's
magnetic field. (g) The opposed slope of two connected cylinders create the moment around axis z. (h)
Toroidal levitator. The closing of different parts of toroid create the different forces in these parts. That
allows creating the slope of apparatus and horizontal force in any direction (include the value of the
force).
The problem can be only apparent when we have cylindrical motionless thruster-levitator.
When we move in West-East or East-West directions, we have full force F. When we move
South-North (or back) and the main direction of an electric currency in thruster is same as the
direction of the Earth's magnetic lines, the force F may be closed to zero (see eq. (1)). More
exactly, a butt-end of the levitate cylinder crosses the magnetic lines and produce the force,
but usually the butt-end area is significantly less than the side area of the cylinder and this
force is small. Only toroidal levitator has same l in any direction. This defect may be
corrected by many means. For example, the AB engine is turning and have West-East
direction for any speed direction of vehicle; the vehicle has ferro-magnetic antennas (which
change the local direction of the Earth's magnetic lines, Figure 4h)., the vehicle has zig-zag
way, and so on. The toroidal thruster (Figure 3) does not have this problem.
4. Ferro-magnetic concentrator of outside magnetic lines. This innovation may be very
useful. Ferro-magnetic matter collects the magnetic lines (magnetic field, magnetic flow). The
electromagnetic induction is
14 Alexander Bolonkin
B 0H ,
(4)
where B is magnetic induction in T, is magnetic permeability (in vacuum = 1), 0 =
410-7 is magnetic constant in N/A2
, H is magnetic induction in A/m.
Magnetic induction at the Earth's magnetic equator is 27.1 A/m. The maximum magnetic
permeability are: for iron = 6100. for the steel Э 310 = 36,000 at H = 9.6 A/m (maximum
B = 1.75 T); for permalloy (having 78.5 Ni) = 100,000 at H = 2 A/m, (Bmax = 0.8). For iron
(having 4.3% Si) B = 0.45 T at H = 40 A/m.
In case of a correct design the permeability can increase magnetic field by hundreds or
thousands of times. It is used in ferro-magnetic antennas in small radio receivers. That also
may be used in AB levitator, thruster, and engine for increasing the propulsion force. It is
very important that the ferro-magnetic changes the direction of the magnetic lines near itself.
The radius of collection (when magnetic wire is parallel to magnetic lines) equals
approximately a length of the wire. The typical levitator with magnetic booster is shown in
Figure 5. However, ferromagnetic method still needs more thorough, detailed investigation.
Figure 5. Ferro-magnetic collector of outside magnetic field. Notations: 1 - outside magnetic field, 2 –
ferro-magnetic circuit, 3 - levitator, 4 - magnetic lines, 5 - electric currency.
5. Cooling system. Figure 6 shows some innovative methods of protection for the AB
levitator in outer space (in vacuum). The simplest protection is a super reflective mirror
(Figure 6a) offered by author in 1988 (see [3] Chs. 12, 3A). The superreflectivity screenmirror
gives deep cooling. The usual high reflectivity screen-mirror gives enough cooling
(Figure 6b). The usual multi-screens protection also gives enough cooling (Figure 6c)(see the
computation in Theoretical Section). The Earth's atmospheric levitator needs liquified
nitrogen (or cheaper liquid air, oxygen) cooling system, but by using the super reflectivity
multi-screen protection we have a very small heat flow and need very small amount of liquid
nitrogen.
New Concepts, Ideas and Innovations in Aerospace… 15
Figure 6. Methods of cooling (protection from Sun radiation) the superconductivity levitator (driver,
thruster) in outer space. (a) Protection the levitator (engine) by the high super refletivity mirror. (b)
Protection by high reflectivity screen (mirror) from Sun and Earth's radiation. (c) Protection by usual
multi-screens. Notations: 1 - superconductive wires (engine); 2 - heat protector (super reflectivity
mirror in Figure6a and a usual mirror in Figure 6c); 2, 3 - high reflectivity mirrors (Figure 6b); 4 - Sun;
5 -Sun radiation, 6 - Earth (planet); 7 - Earth's radiation.
6. Magnetic safety for Human life. The intensity of magnetic field used by the levitator is
very high up 60 - 180 T. Is this dangerous for human health? My answer: if we have the
correct design, the offered levitator contains all magnetic field inside the levitator (Figure 7).
Outside of the levitator the magnetic field equals zero!
When the levitator design is correct, the magnetic field 6 from the internal (lower) circuit
equals and opposed the magnetic field 5 from the outer (top) circuit is outside of the levitator.
The magnetic field is located only between the lower and top circuits. Our design of
superconductivity electric storage is different from common superconductivity ground
storages. The first innovation is filling the internal core by a strong matter (stuff) which can
keep the high tensile stress, the second innovation - we have only ONE turn (coil) of wire (the
current superconductivity electric storages have a lot of turns and, as result, they are outward
of the magnetic field).
Figure 7. The magnetic field of the levitator. (a) Cylindrical levitator, (b) Cross section of the toroidal
levitator. Notations: 1 - is cross section of cylindrical levitator; 2 - wire of top part of coil, 3 - wire of
lower part of coil; 4 - magnetic lines; 5 - magnetic intensity fron lower part of coil; 6 - magnetic
intensity from top part of coil (with minus); 7 - internal core from material (dielectric) having a high
tensile stress; 8 - screen from outside (Earth) magnetic field, 9 - envelope; 10 - heat protection; 11 -
cooling system; 12 - superconductivity electric wire and electric currency.
6. Artificial Magnetic field. The possibility of levitation can be increased thousands times
by the artificial magnetic field. If the magnetic field has enough intensity, the people, car can
fly without non-superconductivity levitators, the ground car can receive electric energy from
16 Alexander Bolonkin
variable magnetic field (it is a solution of a problem of an invironment and oil), the city
resident can receive the electricity without wires, orbiting satellites and spaceships can
receive the thrust and energy when they flyby over this region during their flights. That may
be useful for big city having an dense street traffic. The computation of this case is in the
Theoretical section and estimations in the Project section.
Figure 8. Artificial magnetic field. (a) City having the superconductivity electric ring. (b) Variation
intensity of the magnetic field. Notation: 1 - city, 2 - superconductivity electric ring, 3 - fligth man, 4 -
levitator in the form of a flight plate (UFO), 5 - Earth's satellite, 6 - levitative illumination lamp. R =
in Eq. (16).
3. THEORY AND COMPUTATION
1. Computation (Estimation) of the Levitation Force, Storige Energy, and
Weight of Thruster
For estimation, the following equations of magnetodynamics are used:
F ilBn
, B 0H, H i / 2R
(5)
where all magnitudes are noted in the equations (1)-(4). The new magnitude R is the internal
radius of cylindrical tube or toroid, m.
The important values presented the AB levitator also can be received from
magnitodynamics. They are
g
w
H
B
v w
w
w
B
w
m
S
m
S
v
v
m
max
0
max
0
2
, , 2 ,
2
(6)
New Concepts, Ideas and Innovations in Aerospace… 17
where wv
is volume density of energy, J/m3
, that is also internal pressure into energy storage
in N/m2
; wm is mass density of energy releted to wire mass, J/kg; s
is density of stuff, kg/m3
;
vmax is impulse of levitator stuff, m/s; Hmax is maximum altitude which the stuff can self-lift at
Earth, m. These values show the energetic properties of syperconductivity stuff. Computation
of them are presented in Figures (9)-(11).
The mass of the levitation engine is sum of stuff, wire, cover and cooling and control
systems. If engine is intended for great acceleration and does not need large storage of
energy, the main mass is wire. If device is designed as big storage of electric energy, the main
mass is stuff (80 - 95%). If device operates in outer space, we do not need a cooling system;
in the atmosphere the cooling system increases the mass of the engine by 10 - 30%.
For engine having large storage energy, the magnitudes of Eq. (6) is better computed for
s - density of stuff. They may be also computed for w is specific mass of wire (coil of
levitator). The value of Eq. (6) may be computed for - density of engine. In this case vmax
and Hmax is maximum speed and maximum altitude which can reach engine without useful
load.
Below are computations of Eq, (6).
Figure 9. Specific mass energy of superconductivity AB levitation engine. These results may be
applied to stuff, wire, and engine.
The AB storage energy is similar to the heating value of a conventional fuel or the
specific energy of a rocket fuel. Automotive gasoline has heating value 40106
J/kg, but
internal combustion engine has efficiency coefficient about 0.3. That way we use only 12106
J/kg. More over, the combustion engine requires oxygen (air) and contaminates the Earth's
atmosphere. The liquid rocket fuel (fuel + oxidizer) has about 12106
J/kg, the solid-rocket
18 Alexander Bolonkin
fuel has about 8106
J/kg. As you see (Figure 9), the superconductive storage is the same with
the rocket fuel. but it is sufficiently more for B > 250 T. Our advantage is 100% efficiency,
absence of air pollution and multi-using, because we can recharge the storage device many
times.That has also good prospect because then we can have greater safety maximum B and
more strong stuff of energy storage in the future (nanotubes).
Figure 10. Specific impulse of supercondutivity engine. These results may be applied to wire, stuff and
engine.
The specific impulse of current rocket fuel is about 2000 2500 m/s for solid fuel,
30003200 m/s for liquid fuel, and up 4000 m/s for hydrogen fuel. In our case, impulse is
about 50,000 100,000 m/s, in 20 40 times more (Figure 10). Some electric propulsion has
high impulse (10,00030,000 m/s), but they are technically complex, need large electric
energy, and produce only a small thrust. Our propulsion contains energy in its electric
storage, can have a big thrust and can be charged distantly from the Earth by artificial
magnetic field.
2. Data
Magnetic field. Magnetic induction at the Earth's magnetic equator is 27.1 A/m (B =
3.410-5
T), at the magnetic pole H = 52.5 A/m. In some regions (for example, near Kurs,
Russia) H 100 A/m. Average Earth's magnetic field is about 510-5
T. Earth's field pulses
with friquency 0.1 100 Herzs and amplitude 1%. That may be uses for getting energy.
Magnetic intensity at very high altitude is presented in Figure 12, [5], p. 133. We will use B =
3.410-5
T in our projects up to the altitude 500 km. The closed magnetic field has the small
Martian satellite Phobos. The Sun, Mars and Jupiter have magnetic fields and magnetic stars
New Concepts, Ideas and Innovations in Aerospace… 19
have powerful fields too. The White Dwarf star has B 80,000 T. Neutron star Magnetar
have B up 1011 T.
Figure 11 shows the volume density of energy and magnetic pressure into magnetic
storage. Before B = 100 T we can use the conventional strong fibers as internal stuff of the
superconductive storage (see Table 2 below), in interval B = 100250 T we must use
whiskers, and over B 250 T we need in nanotubes.
Figure 11. Volume energy of superconductivity storage. The right scale shows the internal pressure
into energy storage.
Figure 12. Earth's magnetic intensity far from the Earth's center.
20 Alexander Bolonkin
There are hundreds of new superconductivity matters (type2) having critical temporature
70 120 K and more.
Some of the superconductable material are presented in Table 1 (2001). The widely used
YBa2Cu3O7 has mass density 7 g/cm3
.
Table 1. Transition temperature Tc and upper critical field Hc2(0) of some examined
superconductors [4], p. 752.
Crystal Tc (K) Hc2 (T)
La 2-xSrxCuO4 38 80
YBa2Cu3O7 92 150
Bi2Sr2Ca2Cu3O10 110 250
TlBa2Ca2Cu3O9 110 100
Tl2Ba2Ca2Cu3O10 125 150
HgBa2Ca2Cu3O8 133 150
The last decisions are: Critical temperature is 176 K, up 183 K. Hanotube has critical
temperature 12 - 15 K, Some organic matters has temperature up 15 K. Polypropylene, for
example, is normally an insulator. In 1985, however, researchers at the Russian Academy of
Sciences discovered that as an oxidized thin-film, polypropylene can have a conductivity 105
to 106
higher than the best refined metals.
Boiled temperature of liquid nitrogen is 77.3 K, air 81 K, oxygen 90.2 K, hydrogen 20.4
K, helium 4.2 K [6].
Unfortutately, most superconductive material is not strong and needs a strong covering.
Material strong. Let us consider the following experimental and industrial fibers,
whiskers, and nanotubes:
1. Experimental nanotubes CNT (carbon nanotubes) have a tensile strength of 200
Giga-Pascals (20,000 kg/mm2
). Theoretical limit of nanotubes is 30,000 kg/mm2
.
Young‘s modulus is over 1 Tera Pascal, specific density =1800 kg/m3
(1.8 g/cc)
(year 2000).
For safety factor n = 2.4, = 8300 kg/mm2 = 8.3×1010 N/m2
, =1800 kg/m3
,
(/)=46×106
. The SWNTs nanotubes have a density of 0.8 g/cm3
, and MWNTs have
a density of 1.8 g/cm3
(average 1.34 g/cm3
) Unfortunately, the nanotubes are very
expensive at the present time (1994).
2. For whiskers CD = 8000 kg/mm2
, = 3500 kg/m3
(1989) [3, p. 33]. Cost about
$400/kg (2001).
3. For industrial fibers = 500 – 600 kg/mm2
, = 1800 kg/m3
, = 2,78×106
. Cost
about 2 - 5 $/kg (2003).
Figures for some other experimental whiskers and industrial fibers are given in Table 2.
New Concepts, Ideas and Innovations in Aerospace… 21
Table 2. Tensile strength and density of whiskers and fibers
Material
Whiskers
Tensile
strength
kg/mm2
Density
g/cm3 Fibers
Tensile
strength
kg/mm2
Density
g/cm
3
AlB12 2650 2.6 QC-8805 620 1.95
B 2500 2.3 TM9 600 1.79
B4C 2800 2.5 Thorael 565 1.81
TiB2 3370 4.5 Alien 1 580 1.56
SiC 2100-4140 3.22 Alien 2 300 0.97
Al oxide 2800-4200 3.96 Kevlar 362 1.44
See Reference [3] p. 33.
3. Computation (Estimation) Method
For estimation AB levitator the author recommends the following method based on Eq.
(4) and on usial equations for volum, mass area, etc:
(1) Take the need payload (or mass needs in movement) mp , safety magnetic intensity B,
and dencity storige stuff and wire s , w (You can use the Tables 1, 2). You find by
Eq. (5) (or by Figs. 9-11) the magnitudes wv, wm , vmax, Hmax . Check up the tensile
stress of stuff from the internal magnetic pressure p = wv
in N/m2
or p = 10-7
wv
in
kg/mm2
(Figure 9).
(2) Take the need flight data: altitude H < Hmax , speed V < vmax , range L (H in m, V in
m/s, L in m). The air drag D (in N) of your vehicle, the full mass mx (in kg), or stuff
mass ms (in kg) of your vehicle may be estimated by equations:
w V g H
m V g H DL E
m k
V g H
m w DL E
S m
V
D C
m
p i n
s
s m i n
x x
2
2
2
2
0.5
(0.5 )
,
0.5
,
2
(7)
where Cx 0.02 0.7 is coefficient of air drag; = 1.225 kg/m3
is air density at altitute H
0; S is typical area of vehicle, m2
, for example, cross-section or wing area; k 1 2.1 reserve
coefficient for lift force; Ein expenditure the energy for internal needs (for example, light), in
J/kg; g = 9.81 m/s2
; mp is useful mass of the vehicle, kg.
Equation (7) are recived from an energy balance of the levitation vehicle for k = 1.
mx V gH DL Ei n
wmms mx
mp ms
(0.5 ) ,
2
(8)
Look your attention in the second Eq. (7): if we do not move our apparatus, the mass it
may be infinity. That means we can suspended our device (for example translator) in given
point (V = 0) and does not spend energy its support (exsept stabilization and cooling).
(3) Find the minimal (internal) radius Rm of levitator (AB engine) and minimal currency
im for lift force F = gmx , l = 2h:
22 Alexander Bolonkin
n
m
n
m
h B
F
i
h B B
F
R
2
,
4
0
(9)
where h is the longth (height) of levitator cylinder or small diameter of toroid, m.
(4) Find volume v, mass ms (weight), and thickness of stuff of the cylindrical storage
stuff:
R
v
r
Rh
v
m v
m
E
E m m w v
Rh
m
S s
v
x p m
S
S
2
1
,
2
, or ( ) , , ,
2
(10)
where E is energy into electric storage, J; R > Rm is average radius of cylinder or toroid, m; s
is density of storage stuff, kg/m3
, r is small radius of toroid, m.
(5) Find the cross-section s and mass mw of superconductivity wire:
w w
s i/ j, m 2(h)s
(11)
j 105 A/mm2
= 1011 A/m2
is dencity of the electric currency in superconductivity wire;
w is density of superconductivity wire, kg/m3
(2000 8000 kg/m3
).
(6) Total weight of levitation engine is sum of mass stuff plus mass wire m = ms + mw. It
must be increased in 10 20% for cooling system and cover.
4) Example of Computation. Levitation of a Flying Human
We want to design a levitation belt to lift a living human weighing 82 kg (Figure 3).
(1) Take the magnetic field into AB levitator B = 60 T; wire density w = 8000 kg/m3
;
For B = 60 T the magnetic internal pressure is p =107
wv = 140 kg/mm2
. As the stuff
may be taken the fiber (Table 2). the stuff density s = 1800 kg/m3
, = 600 kg/mm2
.
The computation gives (Eq. (5) or Figs. (9)-(11) ): wv = 1.4109 J/m3
, wm = wv
/s =
7.8105 J/kg .
(2) Take the flight speed V = 15 m/s = 54 km/s, range L = 100 km =100.000 m, altitude
H = 100 m, Ein = 0, k = 2, h = 0.1 m. Compute the air drag: D = 1.4 N and stuff mass
ms = 0.36 kg (Eq. (7)).
(3) Compute minimal radius and currency in belt: Rm = 0.2 m, i = 1.8108 A (Eq. (7)).
(4) Compute volume, weight, and thickness of AB levitate belt (Eq. (8)): = 1.6 mm .
(5) Compute cross-section and weight of superconductive wire (Eq. (9)) for density of
electric currency j = 105 A/mm2
: s = 1.18103
m
2
, mw = 1.89 kg.
New Concepts, Ideas and Innovations in Aerospace… 23
The sum mass of stuff and wire is about 0.36 + 1.89 kg 2.25 kg. This levitator mass we
must increase about in 0.5 - 1 kg for cover, control and cooling system. The total mass of
levitator is about 3 kg.
The internal diameter is about 39 cm, outer diameter is about 42 cm, height of cylinder
(belt) is about 12 cm (Figure3). Remainder the total lift force (together with man) is 82 kg.
These data are not optimal but acceptable for a market individual small vehicle (belt).
The apparatus is based on current technology and can be made at present time (the many
offered innovations and inventions must be used).
5) Computation of AB Levitation Launcher
For B = 140 T specific impulse of AB engine equals the specific impulse of a liquid
rocket engine. However one quickly decreases (as in the second power) when B increases.
The tensile stress of the stuff also rapidly increases. For B = 140 T it equals 780 kg/mm2
. That
is acceptable for whiskers having maximum up 4000 8000 kg/mm2
. The very high B >
200 T is very efficiency as electric storage but request nanotubes as the stuff.
The levitation launch has a many advantages, but in difference of rockets that does not
spend a fuel mass. The weight of AB-engine is same in beginning and ending acceleration. As
a result, the AB engine for high acceleration apparatus needs many stages of multi-launcher.
I recommend the following order of the estimation. Initially we do not include the wire
mass, cover and the cooling system. Their mass is only 10 - 15% of the stuff mass. We take
into account when we take the increased final useful weight of apparatus in 10 - 15%. They
are included into in increased mass of stuff.
The initial data are: the mass mp, final speed V, and final altitude H of apparatus (satellite,
spaceship, or interplanetary probe). We take the equals distribute speed and altitudes between
stages of the levitation accelerator.
In these conditions the mass of every engine stages may be estimated by equations:
n N
w V N gH N
w
m a m a N
m
m
p
n
n
, 1,2,3,...,
0.5( / ) /
, where ( )
2
(12)
where N is number of stage (n is numbering from payload). This ratio is received from
balance of energy.
The mass of stuff included mass wire, cover and cooling system in every stage may be
estimated as below
m n m a N m n m a n N
n
s n s p
( ) / ( ) or ( ) / ,
1,2,3,...,
(13)
The other values (Rm , im , , s) are computed by equations above.
The example of computation the AB launcher for launching of spaceship m = 20 tons to
Moon and Mars is in Projects section.
24 Alexander Bolonkin
6) Artificial of Magnetic Field
The capability of levitation apparatus may be increased thousand times if we create the
outside strong artificial magnetic field. In powerful artificial magnetic field we can achieve
sustained flight without superconductivity devices. This field is useful in big city having
heavy traffic congestion. The artificial magnetic field may be created by superconductivity
ring of a large diameter. This field may be also useful for spaceship. When they flyby into
artificial magnetic field the force increases hundreds of times.
The data of the artificial magnetic field and flight apparatus may be computed by
equations:
, / , / , / , ,
2 F ilB jlsB jvB v ls m j i s r l s E i r
(14)
where F is lift force, N; i is electric currency, A; l is length of AB engine wire into open
magnetic field, m; B is intensity of the artificial magnetic field, T; j is density of electric
currency of AB engine, A/m2
; v is wire volume of engine, m3
; is wire mass density, kg/m3
; s
is cross-section of wire, m2
; r is wire electric resistance, ; is specific resistance of wire,
.
cm; E is loess of energy into conventional (non-superconductivity) AB engine, J; m is wire
mass, kg.
From Eq. (14) we can receive the following ratios for estimation of a data of the
levitation vehicles (do not having the superconductive wires):
2
2
,
2
j
m
E
g
jB
m
Fkg
(15)
where Fkg is lift force in kg. The number "2" appears because the coil has no active back wire.
Aluminum wire has =2.8108
.m (at room temperature) and mass density = 2800
kg/m3
. The maximum of a currency dencity for non-cooling wire is about j = 107 A/m2
(10
A/mm2
). It is obvious, the first ratio in (14) must be over 1 for the levitation apparatus.
The intensity H of the artificial magnetic field at altitude (Figure 8c) may be computed by
formula
3
2 h
iS H
(16)
where S is area of the ground closed loop ring (enveloped by electric currency), m2
; the
distance h equals approximately altitude for high height (Figure8c, R = h).
Weakness of artificial magnetic field is vertical direction of magnetic lines near ground
surface. The magnetic force has horizontal direction. The levitation apparatus needs magnetic
antennas (Figure 5) for lift force creation (or other method for changing the direction of the
magnetic lines).
New Concepts, Ideas and Innovations in Aerospace… 25
The artificial magnetic field and apparatus lift force may be created by permanent
magnets.
The example of computation the levitation device for the flying individual human into
artificial magnetic field are presented in section "Projects".
7) Computation of the Cooling System
The following equations allow direct computing of the proposed cooling systems.
1) Equation of heat balance of a body in vacuum
2
4
1
100
s
T
qs CS a
(17)
where =1 is absorption coefficient of outer radiation, is reflection coefficient; q is heat
flow, W/m2
(from Sun at Earth's orbit q = 1400 W/m2
); s1 is area under outer radiation, m2
; Cs
= 5.67 W/m2K is heat coefficient; a 0.02 0.98 is blackness coefficient; T is temperature,
K; s2 is area of body or screen, m
2
.
2) Heat flow between two parallel screens
1/ 1/ 1
1
, ,
100 100 1 2
4
2
4
1
a Ca aCS a
T T
q C
(18)
where the lower index 1, 2 shows (at T and ) the number of screens. Every coventional screen
decrease temperature aproximately in two times.
3) When we use the conventional heat protection the heat flow is computed by
equations
q k(T1 T2
), k
(19)
where k is heat transmission coefficient, W/m2K; - heat conductivity coefficient, W/m.K.
For air = 0.0244, for glass-wool = 0.037; - thickness of heat protection, m.
Table 3. Boiling temperature and a heat of varoporation of some relevant
liquids [6]. p.68
Liquid Boiling
temperature, K
Heat varoparation,
kJ/kg
Hydrogen 20.4 472
Nitrogen 77.3 197.5
Air 81 217
Oxygen 90.2 213.7
Carbonic acid 194.7 375
26 Alexander Bolonkin
These data are enough for computation of the cooling systems.
Using the correct design of multi-screens, high reflectivity screen, and vacuum between
screens we can get a very small heat flow and a very small expenditure for refrigerant (some
grams per day in Earth). In outer space the protected body can have low temperature without
special liquid cooling system (Figure 6).
For example, the space body (Figure 6a) with innovative prism reflector [3] Ch. 3A ( =
106, a = 0.9) will have temperature 13 K in outer space. The protection Figure6b gives
more low temperature. The usual multi-screen protection of Figure 6c gives the temperature:
the first screen - 160 K, the second - 75 K, the third - 35 K, the fourth - 16 K.
4. PROJECTS
1. Flying (levitation) human was computed above in Theoretical section.
2. Flying car (see plan and equations above):
1. Take the data: magnetic intencity B = 60 T, s = 1800 kg/m3
, w = 8000 kg/m3
, form
is two cylinders h = 1.5 m, Bn = 3.4105
T.
2. Computation: wv = 1.4109
J/m3
, P = 140 kg/mm
2
, wm = wv
/s = 7.8105
J/kg.
3. For V = 20 m/s = 72 km/h, H = 1000 m, L = 1000 km = 106
m, Ein = 7.2105 W, Cx =
0.08, S = 1.5 m2
, we receive D 30 N, ms = 52 kg for one cylinder.
4. Minimal cylinder radius and currency (for lift force one cylinder F = 5500 N): Rm =
0.172 m, i = 5.16107 A.
5. Thickness of stuff: = 17.8103
18 mm.
6. Cross-section and mass of wire (one tube) for currency density j = 105 A/mm2
: s =
5.16 cm2
, mw = 12.4 kg.
7. Total mass of levitation engine (two tubes): m = 1.12(52+12.4) 142 kg.
The levitation engine may be designed as two tubes which join to any CURRENT cars.
The internal combustion engine, transmission, fuel tank may be removed.
The offered AB-engine not only saves the planetary invironment, releases a country from
oil dependence, one spends energy sometimes less than when using a liqued fuel. The drag of
usual car endures the friction of its wheels on the ground and some air drag. For friction
coefficient 0.1 the friction drag for car mass 1000 kg is about 1000 N plus air drag 30 - 100
N. The flying car does not have wheel friction. That means AB car spends an energy for
moving that is 20 times less than a conventional car. Make corrections that internal
combustion engine has efficiency coefficient about 0.3 and a design can be done for a special
flight light (without usual engine, transmission, wheels, etc.) car with small aerodynamic drag
and AB engine has 100% efficiency and return the energy spent to lifting and acceleration of
car. Moreover the AB car can fly in a straight line. If planet without atmosphere has natural or
artifical magnetic field you can have a free flight to any planet place.
No problem to organize the air traffic for large numbers of the flying cars or flying
people as is done for current aircraft and spacecraft. For example, in diapason of altitude 100-
New Concepts, Ideas and Innovations in Aerospace… 27
200 m flying cars move from West to East, in diapason 200 -300 m they move from North to
South, in next diapason - from East to West and so on.
3. Lavitation Aircraft with AB engine. Design the aircraft having a flight weight 100 tons.
1. Take mp = 105
kg, B = 120 T, s = 2300 kg/m3
, w = 8000 kg/m3
.
2. Computation: wv = 5.7109
J/m3
, P = 570 kg/mm2
, wm = wv
/s = 2.48106
J/kg .
3. For V = 250 m/s = 900 km/h, H = 30,000 m, L = 10,000 km = 107
m, Ein = 3.6105
W, Cx = 0.06, S = 9.07 m2
, h = 14.5 m (cylindrical tube is part of fuselage), we
receive D 300 N, ms = 2940 kg.
4. Minimal cylinder radius and currency (for lift force of one cylinder F = 106 N): Rm =
1.69 m, i = 109 A.
5. Thickness of stuff: = 6.44103
6.44 mm.
6. Cross-section and mass of wire (one tube) for currency density j = 105 A/mm2
: s =
0.01 m2
, mw = 112 kg.
7. Total mass of levitation engine: m = 2940 + 122 3062 kg. Together with cooling
system the mass of AB engine will be about 3.3 tons. The same way may be
computed hypersonic or space aircraft. They can operate at very high altitude and
have a small drag. That means they will spend very little energy per flight. If the
aircraft will fly across space, the spent energy will be very small. We can also design
the levitation space submarine with AB engine.
Figure 13. Possible form of levitation aircraft.
4. Levitation (stasionary) Satellite with AB engine. Compute AB engine for self-launch
levitation stationary communication satellite located at an altitude of 40 km. This satellite can
service a region within a radius of 700 km.
28 Alexander Bolonkin
1. Take the data: magnetic intensity B = 60 T, s = 1800 kg/m3
, w = 8000 kg/m3
, form
is cylinders, h = 0.2 m, Bn = 3.4105
T, useful mass 80 kg.
2. Computation: wv = 1.4109
J/m3
, P = 140 kg/mm2
, wm = wv
/s = 7.8105
J/kg.
3. For V = 0, H = 40,000 m, L = 0, Ein = 0, k = 2. we receive ms = 168.4 kg for one
cylinder.
4. Take the total mass of apparatus 280 kg. Minimal cylinder radius and currency (for
lift force one cylinder F = 2600 N): Rm = 0.63 m, i = 1.91108 A.
5. Thickness of stuff: = 0,12 m.
6. Cross-section and mass of wire (one tube) for currency density j = 105 A/mm2
: s =
1.9103
m, mw = 1 kg.
7. Mass of levitation engine : m = 1.1(168,4+1) 184.1 kg. Total mass of satellite is
184.1+80=264.1 280 kg.
Figure 14. Possible form of levitation satellite and levitation vehicle.
6. Space Launch system. Compute the AB space launcher for launching the spaceships of
mass 20 tons to Moon and Mars.
1. Take payload mp = 25 tons =25103
kg, B = 140 T, Bn = 3.4105
T, s = 2300 kg/m3
,
w = 8000 kg/m3
, final speed V = 11 km/s, final altitude is H = 200 km, number of
stages N = 15.
2. Compute: wv = 7.8109
J/m3
, P = 780 kg/mm2
, wm = wv
/s = 3.4106
J/kg , vm = 2600
m/s, Hm = 340 km.
3. Compute by Eq. (11) the mass of the last (N) stage: a = 1.1724, m(N) = 272 tons.
4. Compute the minimal radius and minimal currency of last stagy for length h = 20 m,
F = 2.72106 N: Rm = 2.86 m, i = 2109 A, ms(N) = 40103
kg.
5. Thickness of stuff: = 14103
14 mm.
6. Cross-section and mass of wire for currency density j = 105 A/mm2
: s = 0.02 m2
, mw
= 6400 kg.
New Concepts, Ideas and Innovations in Aerospace… 29
7. Total mass of the last stage without upper stages is 40 tons, total 272 tons.
All stages can be re-used for thousands of launchs. They can await the spaceship in flight
and maintain levitation positions. When the spaceship returns and its mass is same to the
launch mass, then all stages brake the spaceship and restore its energy. After landing they
readied for the next free launch. Note, all stages are the thickness tubes which are inserted one
into other.
Figure 15. Possible form of space system.
7. Artificial Magnetic field. Let us take the supercoductive closed-loop cable-ring having
radius R = 10 km inside a big city. The efficiency radius of this ring is about 20 km or the
diameter of artificial magnetic field is about 40 km. That is enough for any big city. If the
cross-section area of the cable is 0.15 m2
and currency density is 1011 A/m2
, the magnetic
intensity B = oi/2R is about 1.9 T. Take for levitation devices the aluminum wire having
=2.8108
.m and = 2800 kg/m3
, j = 0.35106 A/m2
, B = 1.8. From ratios (15) we receive
Fkg/m = 11.5 or 115 N/kg, E/m = 2.45 W/kg.
If mass of flying man is 80 kg and together with levitation device that is 100 kg, the mass
of wire will be mw = 100/11.5 = 8.7 kg and the heat expenses of energy in levitation is 245 W
or 8.8105 J in hours. The good rechargable battery has storage of an energy about 70 Wh/kg
= 2.5105 J/kg. That means the 8 kg battery has energy E = 20105 J. That is enough for two
hours of flight. If it has a speed V = 15 m/s = 54 km/h, our range equals more 100 km. The air
drag for this speed requires about 1.4105 J. The full weight of levitation device is about 17 -
18 kg.
The levitation car may be computed similarly, but it needs a small conventional engine
for support of car battery. If we are not limited to strong expenditures of energy, the current
density may be increases from 0.35 A/mm2
up to 10 A/mm2
. That decreases the mass of wire
by 30 times, but increases the heat loss in wire by two orders.
30 Alexander Bolonkin
The constant artificial magnetic field does not need in support energy. That also may be
used as storage electric energy for big city. If we use the supercondutivity devices, the
artificial magnetic field may be small.
If magnitic field is made variable and one direction of magnetic intensity (see Figure 8b),
this magnetic field will be able to pump the energy in the levitation engines and any special
electric receivers having closed loop coil. We will not need a complex electric grid, which is
in any big city. We can significently improve the parameters of city ring and flight nonsuperconductivity
devices if we use well ferro-magnetic matter. If we use permanent magnits
for ground and apparatus, the human, vehicles can flight withotut spenging a large energy.
8. Magnetic highway. The supercontactive cabel (having cross-section area s = 2.5 cm2
, j
= 105 A/mm2
, B = 140 T ) instelled on ground creates the magnetic intensity B = 1 T in
distance up 5 m. The cars, tracks having enogh constant magnets (or AB-engine) can flight
along this highway.
The initial data in all our projects are not optimal. Our aim - it shows that AB engine may
be designed by current technology.
DISCUSSION
The simple experiments was made by physicist Dr.Sci. Mark Kriker are shown the
magnetic force appear when a back currency wire is included into ferromagnetic tube. The
sketch of Krinker‘s instellation is shown in Fig.16. The photo of instellation is presented in
Fig. 17.
The force change the direction when we change the direction of magnetic lines include
movement in gradient and anti-gradient of magnetic intencity. That exclude an explanation of
movement by a gradient of the magnetic field.
For measure this force we need more complex and more precise devices and equipment.
Figure 16. Sketch of Krinker‘s instellation for demonstration the magmetic force when back
wire protected from the outer magnetic field. Data: ferromagnetic cylinder has: 28x18x10 mm;
total wire of spool has length 1 m, impuls currency about 10 A; Magnetic field about 0.01 T.
New Concepts, Ideas and Innovations in Aerospace… 31
Figure 17. Instellation for Krinker‘s experiment. Additional devices use for non-contact
turning in an electric currency.
The offered AB engines may be made by existing technology. We have a superconductivity
material (see Table 1), the strong artificial fibers and whiskers (Table 2), the light cooling
system (Table 3) for the Earth's atmosphere, and the radiation screens for outer space. The
Earth has enough magnetic field, the Sun and many planets and their satellites (as Phobos
orbiting Mars) has also magnetic field. The magnetic stars has powerful magnetic field, for
example, White Dwarfs have magnetic field up B = 80,000 T, the neutron stars Magnetar
have gigantic magnetic field up 1011 T. They may be used for interstellar flight. No problem
to create the artificial magnetic field [6] on asteroids and planet satellites (for example, to
create local artificial magnetic field on the Earth or Moon). We have a very good perspective
in improving our devices because—especially during the last 30 years—the critical
temperature of the supercoductive material increases from 4 K to 186 K and no theoretical
limit for further increase. Moreover, Russian scientists received the thin layers which have
electric resistance at room temperature in million times less then the conventinal conductors.
We have nanotubes which will create the jump in AB engines, when their production will be
cheaper. The current superconductive solenoids have the magnetic field B 20 T.
AB engines can instigate a revolution in air, ground, sea and space transport. They allow
individuals to fly as birds, almost energy-free (without loss of total energy or small expenses
of energy) flight with hypersonic and space speed to any point of Earth and to other planets.
The interstellar probes can use the magnetic fields of satellites and planet for braking and
acceleration.
32 Alexander Bolonkin
The AB engines solve the environment problem because they do not emit or evolve any
polluting gases. They are useful in any solution for the oil-dependence problem because they
use electricity and spend the energy for flight and other vehicles (cars) many times less than
conventional internal combustion engine. In difference of a ground car, the levitation car
flights in straight line to object.
The AB engines create the revolution in communication by the low altitude stationary
suspended satellites, in energy industry, and especially in military aviation. They are very
useful in lighting of Earth by additional heat and light Sun radiation because, in difference
from conventional mobile space mirrors, they can be suspended over given place (city) and
service this place.
It is interesting, the toroidal AB engine is very comfortable for flying discs (UFO!) and
have same property with UFOs. That can levitate and move in any direction with high
acceleration without turning of vehicle, that does not excrete any gas, jet, that does not
produce a noise.
Note, physicists have discussed for a long time the possible changing of weight the
superconductivity magnet. Some of them are getting the changing and announce it as
revolutionary discovery; others are repeating the test and getting negative results. The reason
may be in different position their magnets and screening of part superconductivity coil about
direction of the Earth's magnetic field.
CONCLUSION
We must research and develop these ideas as soon as possible. They may to accelerate the
technical progress and improve our life. There are no known scientific obstacles in the
development and design of the AB engines, levitation vehicles, high speed aircraft, space
launches, low aititude stationary communication satellites, cheap space trip to Moon and
Mars and so on.
REFERENCES
(see some Bolonkin's articles in Internet: http://Bolonkin.narod.ru/p65.htm and
http://arxiv.org search "Bolonkin")
[1] Bolonkin A.A., "Theory of Flight Vehicles with Control Radial Force". Collection
Researches of Flight Dynamics. Mashinostroenie Publisher, Moscow, 1965, pp.79-118
(in Russian). International Aerospace Abstract A66-23338# (in English). The work
contains theory of flight vehicles with control gravity.
[2] Bolonkin A.A., "Electrostatic Levitation on the Earth and Artificial Gravity for Space
Ships and Asteroids". Paper AIAA-2005-4465, 41-st Propulsion Conference, 10-13 July
2005, Tucson, AZ, USA. The work contains theory of electroctatic levitation of flight
vehicles and creating artificial gravity in space ships without rotation of apparatus (see
also [3], Ch. 15).
[3] Bolonkin A.A., Non-Rocket Space Launch and Flight, Elsevier, 2006, 488 pgs. The
book contains theories of the more then 20 new revolutionary author ideas in space and
technology.
[4] AIP, Physics Desk Reference, 3-rd Ed. Springer, 2003.
[5] Koshkin N.I. Reference book of elementary physics, Nauka, Moscow, 1982 (Russian).
[6] Bolonkin A.A., AB Levitrons and their Applications to Earth's Motionless
Satellites. http://arxiv.org search ―Bolonkin‖, 2007.
New Concepts, Ideas and Innovations in Aerospace… 33
ATTACHMENT TO PART A, CHAPTER 1
Earth's magnetic field interaction with solar wing.
Magnetic field of Sun.
34 Alexander Bolonkin
Attachment to Part A, Ch. 1. Possible forms of MagFly, Space Ships and Space Station
New Concepts, Ideas and Innovations in Aerospace… 35
36 Alexander Bolonkin
New Concepts, Ideas and Innovations in Aerospace…
Chapter 2
ELECTROSTATIC AB-RAMJET SPACE
PROPULSION
ABSTRACT
A new electrostatic ramjet space engine is proposed and analyzed. The upper
atmosphere (85 -1000 km) is extremely dense in ions (millions per cubic cm). The
interplanetary medium contains positive protons from the solar wind. A charged ball
collects the ions (protons) from the surrounding area and a special electric engine
accelerates the ions to achieve thrust or decelerates the ions to achieve drag. The thrust
may have a magnitude of several Newtons. If the ions are decelerated, the engine
produces a drag and generates electrical energy. The theory of the new engine is
developed. It is shown that the proposed engine driven by a solar battery (or other energy
source) can not only support satellites in their orbit for a very long time but can also work
as a launcher of space apparatus. The latter capability includes launch to high orbit, to the
Moon, to far space, or to the Earth atmosphere (as a return thruster for space apparatus or
as a killer of space debris). The proposed ramjet is very useful in interplanetary trips to
far planets because it can simultaneously produce thrust or drag and large electric energy
using the solar wind. Two scenarios, launch into the upper Earth atmosphere and an
interplanetary trip, are simulated and the results illustrate the excellent possibilities of the
new concept.
Keywords: Electrostatic ramjet space engine, ramjet space thruster, orbit launcher.
Earth orbit space propulsion. Interplanetary propulsion, interstellar propulsion, AB-Ramjet
space engine.
INTRODUCTION
General. At present, we use only one method of launch for extra-planetary flight that
being liquid-fuel or solid-fuel rockets. This method is very complex, expensive, and
dangerous.
Presented as Bolonkin‘s paper AIAA-2006-6173 to AIAA/AAS Astrodynamics Specialist Conference, 21-24
August 2006, USA.
38 Alexander Bolonkin
The current method of flight has reached the peak of its development. In the last 30 years
it has not allowed cheap delivery of loads to space nor made tourist trips to the cosmos, or
even to the upper atmosphere, affordable. Space flights are very expensive and not
conceivable for the average person. The main method used for electrical energy separation is
photomontage cells. Such solar cells are expensive and have low energy efficiency.
The aviation, space, and energy industries need revolutionary ideas which will
significantly improve the capability of future air and space vehicles. The author has offered a
series of new ideas [1 - 60] contained in a) numerous patent applications, [3 - 18] b)
manuscripts that have been presented at the World Space Congress (WSC)-1992, 1994 [19 -
22], the WSC-2002 [23 - 32] , and numerous Propulsion Conferences, [32 - 38] and c) other
articles [39 - 59]
In this article a revolutionary method and implementations for future space flights are
proposed. The method uses a highly charged open ball made from thin film which collects
space particles (protons) from a large area. The proposed propulsion system creates several
Newtons of thrust and accelerates space apparatus to high speeds.
History. The author started closed research in this area as far back as 1965 [1 - 2]. A
series of patent applications [3 - 18] submitted during 1982 -1983 documented several
methods and implementations for space propulsion and electric generators using solar wind
and space particles. In 1987 these ideas were described in Report ESTI [16]. In 1990 the
author published brief information about this topic [17] (see pp. 67 - 80) and in 1992 -1994 he
reported on further research at the World Space Congresses -1992, 1994, 2002 [19 - 32] and
his manuscripts [33 - 59].
Brief information about space particles and space environment. In Earth's atmosphere at
altitudes between 200 - 400 km (Figure 8), the concentration of ions reaches several million
per cubic cm. In the interplanetary medium at Earth orbit, the concentration of protons from
the Solar Wind reaches 3 - 70 particles per cubic cm. In an interstellar medium the average
concentration of protons is about one particle in 1 cm3
, but in the space zones HII (planetary
nebulas), which occupy about 5% of interstellar space, the average particle density may be
10-20 g/cm3
(107
1/cm3
).
If we can collect these space particles from a large area, accelerate and brake them, we
can get the high speed and braking of space apparatus and to generate energy. The author is
suggesting the method of collection and implementations of it for propulsion and braking
systems and electric generators. He developed the initial theory of these systems.
SHORT DESCRIPTION OF THE IMPLEMENTATION
A Primary Ramjet propulsion engine is shown in Figure 1. Such an engine can work in
one charge environment. For example, the surrounding region of space medium contains the
positive charge particles (protons, ions). The engine has two plates 1, 2, and a source of
electric voltage and energy (storage) 3. The plates are made from a thin dielectric film
covered by a conducting layer. As the plates may be a net. The source can create an electric
voltage U and electric field (electric intensity E) between the plates. One also can collect the
electric energy from plate as an accumulator.
New Concepts, Ideas and Innovations in Aerospace… 39
The engine works in the following way. Apparatus are moving (in left direction) with
velocity V (or particles 4 are moving in right direction). If voltage U is applied to the plates, it
is well-known that main electric field is only between plates. If the particles are charged
positive (protons, positive ions) and the first and second plate are charged positive and
negative, respectively, then the particles are accelerated between the plates and achieve the
additional velocity v > 0. The total velocity will be V+v behind the engine (Figure 1a). This
means that the apparatus will have thrust T > 0 and spend electric energy W < 0 (bias,
displacement current). If the voltage U = 0, then v = 0, T = 0, and W = 0 (Figure 1b).
If the first and second plates are charged negative and positive, respectively, the voltage
changes sign Assume the velocity v is satisfying -V < v < 0. Thus the particles will be braked
and the engine (apparatus) will have drag and will also be braked. The engine transfers braked
vehicle energy into electric (bias, displacement) current. That energy can be collected and
used. Note that velocity v cannot equal -V. If v were equal to -V, that would mean that the
apparatus collected positive particles, accumulated a big positive charge and then repelled the
positive charged particles.
If the voltage is enough high, the brake is the highest (Figure 1d). Maximum braking is
achieved when v = -2V (T < 0, W = 0). Note, the v cannot be more then -2V, because it is full
reflected speed.
AB-Ramjet engine. The suggested Ramjet is different from the primary ramjet. The
suggested ramjet has specific electrostatic collector 5 (Figure 2a,c,d,e,f,g). Other authors said
the idea of space matter collection. But they did not give the principal design of collector.
Their electrostatic collector cannot work. Really, for charging of collector we must move
away from apparatus the charges. The charged collector attracts the same amount of the
charged particles (charged protons, ions, electrons) from space medium. They discharged
collector. All your work will be idle. That cannot work.
The electrostatic collector cannot adsorb a matter (as offered some inventors) because it
can adsorb ONLY opposed charges particles, which will be discharged the initial charge of
collector. Physic law of conservation of charges does not allow to change charges of particles.
The suggested collector and ramjet engine have a special design (thin film, net, special
form of charge collector, particle accelerator). The collector/engine passes the charged
particles ACROSS (through) the installation and changes their energy (speed), deflecting and
focusing them. That is why we refer to this engine as the AB-Ramjet engine. It can create
thrust or drag, extract energy from the kinetic energy of particles or convert the apparatus'
kinetic energy into electric energy, and deflect and focus the particle beam. The collector
creates a local environment in space because it deletes (repeals) the same charged particles
(electrons) from apparatus and allows the Ramjet to work when the apparatus speed is close
to zero. The author developed the theory of the electrostatic collector and published it in [53].
The conventional electric engine cannot work in usual plasma without the main part of the
AB-engine - the special pervious electrostatic collector.
The plates of the suggested engine are different from the primary engine. They have a
concentrically septa (partitions) which create additional radial electric fields (electric
intensity) (Figure 2b). They straighten, deflect and focus the particle beams and improve the
efficiency coefficient of the engine.
40 Alexander Bolonkin
Figure 1. Explanation of primary Space Ramjet propulsion (engine) and electric generator (in
braking),a) Work in regime thrust; b) Idle; c) Work in regime brake. d) Work in regime strong brake
(full reflection). Notation: 1, 2 - plate (film, thin net) of engine; 3 - source of electric energy (voltage
U); 4 - charged particles (protons, ions); V - speed of apparatus or particles before engine (solar wind);
v - additional speed of particles into engine plates; T - thrust of engine; W - energy (if W < 0 we spend
energy).
Figure 2. Space AB-Ramjet engine with electrostatic collector (core). a) Side view; b) Front view; c)
Spherical electrostatic collector (ball); d) Concentric collector; e) cellular (net) collector; f) cylindrical
collector without cover butt-ends; g) plate collector (film or net).
New Concepts, Ideas and Innovations in Aerospace… 41
The central charge can have a different form (core) and design (Figure 2 c,d,e,f,g,h). It
may be:
(1) a sphere (Figure 2c) having a thin cover of plastic film and a very thin (some
nanometers) conducting layer (aluminum), with the concentrical spheres inserted one
into the other (Figure 2d),
(2) a net formed from thin wires (Figure 2e);
(3) a cylinder (without butt-end) (Figure 2f); or
(4) a plate (Figure 2g).
The design is chosen to produce minimum energy loss (maximum particle transparency -
see section "Theory"). The safety (from discharging, emission of electrons) electric intensity
in a vacuum is 108 V/m for an outer conducting layer and negative charge. The electric
intensity is more for an inside conducting layer and thousands of times more for positive
charge.
The engine plates are attracted one to the other (see theoretical section). They can have
different designs (Figure 4a - 4d). In the rotating film or net design (Figure 4a), the
centrifugal force prevents contact between the plates. In the inflatable design (Figure 4b), the
low pressure gas prevents plate contact. A third design has (inflatable) rods supporting the
film or net (Figure 4c). The fourth design is an inflatable toroid which supports the distance
between plates or nets (Figure 4d).
Electric gun. The simplest electric gun (linear particle accelerator) for charging an
apparatus ball is presented in Figure 4. The design is a long tube (up 10 m) which creates a
strong electric field along the tube axis (100 MV/m and more). The gun consists of the tube
with electrical isolated cylindrical electrodes, ion source, microwave frequency energy
source, and voltage multiplier. This electric gun can accelerate charged particles up 1000
MeV. Electrostatic lens and special conditions allow the creation of a focusing and selffocusing
beam which can transfer the charge and energy long distances into space. The
engine can be charged from a satellite, a space ship, the Moon, or a top atmosphere station.
The beam may also be used as a particle beam weapon.
Figure 3. Possible design of the main part of ramjet engine. a) Rotating engine; b) Inflatable engine
(filled by gas); c) Rod engine; d) Toroidal shell engine, e) AB-Ramjet engine in brake regime, f) ABRamjet
engine in thrust regime. Notation: 10 - film shells (fibers) for support thin film and creating a
radial electric field; 11 - Rods for a support the film or net; 12 - inflatable toroid for support engine
plates; 13 - space apparatus; 14 - particles; 15 - AB-Ramjet.
42 Alexander Bolonkin
Approximately tens years ago, the conventional linear pipe accelerated protons up to 40
MeV with a beam divergence of 10-3
radian. However, acceleration of the multi-charged
heavy ions may result in significantly `more energy.
Figure 4. Electric gun for charging AB-Ramjet engine and transfer charges (energy) in long distance. a)
Side view, b) Front view. Notations: 1 - gun tube, 2 - opposed charged electrodes, 3 - source of charged
particles (ions, electrons), 4 - particles beam.
At present, the energy gradients as steep as 200 GeV/m have been achieved over
millimeter-scale distances using laser pulsers. Gradients approaching 1 GeV/m are being
produced on the multi-centimeter-scale with electron-beam systems, in contrast to a limit of
about 0.1 GeV/m for radio-frequency acceleration alone. Existing electron accelerators such
as SLAC could use electron-beam afterburners to
increase the intensity of their particle beams. Electron systems in general can provide tightly
collimated, reliable beams while laser systems may offer more power and compactness.
THEORY OF SPACE AB-RAMJET PROPULSION
The main part and innovation of the suggested system is the charged core. That may be a
charged ball (Figure 2 c,d,e), a cylinder (Figure 2f), or a plate (Figure 2g). The big charge has
some problems in space. We consider the major problems below.
1. Blockading of the Ball Charge (AB-Radius)
Blockading of the charge core by unlike particles is the main problem with this method.
The charge on the core attracts unlike particles and repels like particles. The opposite charged
particles accumulate near the core and block its charge. As a result, the area of ball (charged
core) influence is many times less than the area of the interaction of the ball and the particles
when there is no blockading. The forces are thus greatly reduced.
The author of this work proposed two models for estimation of the efficient charge
radius, named AB-radius (radius of neutral working charge). That radius is analog of the
Debaev shield radius for single charged particles in plasma theory. In the first model, the
radius of the efficient area is computed as the area where particles of like charge to the ball
are absent and the density of opposite-charged (unlike) particles is the same as the space
medium. This model gives the lower limit of the efficient area. In the second model, the
radius of the efficient area is computed as the area where the density of unlike particles is less
than the space medium density because the unlike particles inside the efficient area have
generally higher velocity than a those outside this area. The neutral area (neutral sphere) in
model 2 is larger than in model 1. Model 2 is better, but this problem needs more detailed
research.
New Concepts, Ideas and Innovations in Aerospace… 43
It is possible to find the minimum distance which space electrons can approach a
negatively charged ball. The full energy of a charged particle (or body) is the sum of the
kinetic and potential electric energy. Any change of energy equals zero:
0
2
,
1 1
0, , ,
2
2
2
2
r
mV kqQ
r
kqQ
r
E kqQ
r
q Q E E Fdr F k
mV
p
r
p p
(1)
where m is the mass of a particle [kg] (mass of a proton is mp = 1.67.
10 -27 kg, mass of an
electron is me = 9.11.
10 -31 kg); V is the speed of particle [m/s] (for solar wind Vs = 300 - 1000
km/s); Ep is the potential energy of a charged particle in the electric field [J]; F is the electric
force, N; q is the electrical charge of a particle [C] (q = 1.6×10 -19 C for electrons and
protons); k = 9×109
is coefficient, r is the distance from a particle to the center of the ball [m];
Q is ball charge [C].
From equation (1) the minimum distance for a solar wind electron is (m = me
, V = Vs):
m
a E q K
k
a E
Q
m
kqQ K
m V
a E q
V
K
m V
kqQ
r
s e s
2 2
2
2
min 2 2
, where , ,
2 2 2
(2)
where K is a coefficient; me
is electron mass; Vs
is the solar wind speed [m/s]; a is the radius
of ball [m]; E is electrical intensity at the ball surface [V/m]. The maximum electrical
intensity of the open negative bare charge is about 108
- 2108 V/m in a vacuum.
For a = 6 m, E = 108 V/m, Vs = 4105 m/s we have rmin 8106
km. The minimum
distance of a hyperbolic particle trajectory from the punctual charged core is
e
p
r
c
K
H
K
c
H V e
K
c
p
m
a qE
c R V K
h
h
h h
h e h
1
, , , , ,
2 min
2
2
2 2
(2a)
where Re
is AB-radius efficiency of charged ball (see Eq. (4 - 5) later). All other values are
parameters of the hyperbole and computed in (2a). The minimal radius of (2a) gives the lower
estimation for the required radius of the engine plates. The above estimation of maximum
plate radius for speed less 1000 km/s may be found from the equation
qa E
R V m
R
e
p 2
2 2
(2b)
2. Minimumal Neutral Sphere (AB-Radius) around a Charged Ball
a) Model 1. Constant particle density. The charge density of the unlike space plasma
particles inside a neutral sphere is equal to the density of solar wind. The minimum radius of
the neutral sphere is
44 Alexander Bolonkin
d Nq
k d
a E
d
Q
Q R
n
d R
n
6
3
2
3
3
, 10
4
3
4
3
,
3
4
(3)
where d is density of solar wind [C/m3
]; Rn is the minimum radius of the neutral sphere [m];
N is the number of particles in cm3
.
b) Model 2. Variable particle density. Density of the unlike particles inside the neutral
sphere will be less than the density of solar wind particles because the particles are strongly
accelerated by the ball charge to approximately the speed of light. The new density and new
corrected radius can be computed in the following way:
1) The speed of protons along a ball radius is (in the system connected to the particles)
0
2
0
2 1 1
2
r r
Vr
r V K
(4)
where V0 = Vs - proton speed at an initial radius of R >> Rn, and Rn is the radius of the neutral
sphere.
2) Particle charge density, dp, along a ball radius is
0
0 6 2
, 10 / ,
( ) S
S
d Nq s s
V r
V
d d p o
r
p
p o
(5)
where S is distance from the Sun in AU; S0 = 1 AU; s is relative distance from the Sun; dpo is
density at 1 AU.
3) Charge of the neutral sphere along a sphere radius is
dr
V r
r
Q Q d V
R
a r
r po
2
4 0
(6)
4) The AB-radius of the neutral (blocking) sphere can be found from the condition Qr = 0.
Note. For our estimation we can find it using the stronger condition Qr = 0.5Q, and call it
the efficiency radius Re of the charge Q. We use the stronger condition because model 2 may
yield a more accurate result (with the speed Vr being slower).
The efficiency radius in Model 2 is significantly more than in Model 1. Model 1 gives the
lower estimation of the efficiency radius; model 2 gives the top (more realistic) estimation of
the efficiency AB-radius. In our computation we will use the model 2 with the note above.
3. Computation of Main Parameters of AB-Ramjet Propulsion
If we know the efficiency radius and voltage U between engine plates, we can develop
the theory and compute all the main parameters of Space AB-Ramjet. The formulas and final
equations are given below. All values are in metric system (SU).
New Concepts, Ideas and Innovations in Aerospace… 45
1). Additional speed v of particles gained between engine plates.
m
qU qU we get v
mv From 2
2
2
(7)
where m is mass of particle [kg](for proton m = mp = 1.6719-27 kg, for electron m = me =
9.10910-31 kg); q - charge of particle [C], for proton and electron q = 1.610-19 C, U -
electric voltage between plates [V].
2) Mass ms running through engine in one second
ms SVnm 6
10
(8)
where
2
S R
e
is area of engine efficiency [m2
], n is number particles in 1 cm3
(coefficient
106
in (8) transfer n in m3
), V is apparatus (or relative particles speed about apparatus, out of
efficiency area (for example, Solar wind speed))[m/s].
3) Thrust T (or brake force, drag D)[N] of Ramjet engine is
T ms
v, T nSV 2mqU , Dmax
2msV
(9)
The full maximum drag can be easily obtained in the conventional (Figure1) electric
engine. But it is difficult to achieve in the AB-engine because collector of this engine requires
very high voltage, Ub= aE. However, when plate voltage is zero, the AB-engine can easily
achieve a slightly less than maximum drag via
D = c4msV , (9a)
here c4 = 0 - 2 is drag coefficient which depends from charged core. If c4 is less 1, the drag is
easily controlled using the plate voltage U.
4) Currency of particles flow through engine
I nSVq
,
(10)
5) Electric power N of particles flow
N IU or Nb
DV
(11)
where U is voltage between plates, V. This power is negative (we spend energy) when we get
thrust and the power is positive when we brake, Nb is brake power.
6) Voltage of electricity induced in brake regime
v V
q
mv Ub
,
2
2
(12)
46 Alexander Bolonkin
7) Propulsion efficiency coefficient.
a) For Ramjet engine the coefficient of propulsion efficiency equals
V
v
v
v
or
m v m vV
m vV
s s
s
,
1 0.5
1
,
0.5
2
(13)
b) For any rocket engine the coefficient of propulsion efficiency equals
V
v
v
v
v
T V v m
TV m v
TV
s R
s
R
,
2(1 )
1
1
, ( ) ,
0.5
2 2
(14)
Computation of equations (13) - (14) are presented in Figure 5.
Figure 5. Propulsion coefficient of efficiencies for Ramjet and conventional rocket engine (includes
conventional electric rocket thrusters) versus relative jet speed.
As can be seen, the efficiency of the conventional rocket engine seems better than of the
AB-Ramjet. However, full engine efficiency is a product of the propulsion and terminal
efficiencies. The terminal coefficient of the conventional (liquid) rocket engine is large, with
a value of 0.68 (nozzle loss), while the terminal coefficient of the conventional rocket electric
(ion) thruster is small. This is because the rocket ion thruster spends a lot of energy in the
ionization of the jet mass. The proposed AB-engine's terminal coefficient depends on a
transparency coefficient (discussed later) of plates and core and the terminal efficiency can be
high. Note that the rocket propulsion having the high speed of the jet has low efficiency from
an energy viewpoint. The rocket electric thruster with high specific impulse (jet speed) spends
New Concepts, Ideas and Innovations in Aerospace… 47
a significant amount of energy per unit of thrust. The photon rocket has top jet speed and the
worst energy efficiency. The best efficiency ( 1) is achieved by a propulsion system which
repels from a very large mass (for example, a planet). Our AB-Ramjet engine uses outer
space mass. That is very big advantage in comparison to the conventional electric thruster and
rocket which uses its own mass.
Figure 6. Expenses of relative mass (energy) versus relative apparatus speed for a different engines:
photon engine, multi-reflex engine [52] located on the planet surface and located in the apparatus. The
AB-Ramjet located between multi-reflex engine located on the vehicle and photon engine. The curve
depends from a flow of space mass through engine. Transfer efficiency coefficient (mass to energy)
equals 1. Computations made in system coordinate connected with apparatus. The relativistic effect (for
Earth's observer) can change these results for high speed.
8) Final relative speed of different propulsion systems. Assume we can covert mass into
energy and back with an efficiency coefficient of 1. Assume the system coordinate is
connected with apparatus. Compare the relative fuel consumption.
a) Photon engine.
M e M M
M
M
M
c
V
V M V
M
M
c
V mdV cdm f
k k V
, ln , ln , , , , 1
0 0
(15)
where Mk
is final apparatus mass [kg], M0 is start apparatus mass [kg], c is light speed, c =
3108 m/s,
M f
is a spend relative fuel consumption.
b) Apparatus repels from a planet using its own energy (fuel) (for example, multi-reflex
engine [52] located in the apparatus).
48 Alexander Bolonkin
, 1 .
1 0.5
1
1 ,
1
( ) we receive 2 1 2
2
From
2
2 0
0
2
M M
V
M
M M
M
c
V M M c V
M V
f
k
k
k
(16)
c) Apparatus repels from planet using planet energy (fuel) (for example, multi-reflex
engine [52] located on planet surface).
e e f e
e
e
M M V M M
M
M
c
V M c V
M V
,
2
1
w e receive 2 2 ,
2
From 2
0
2
2
(17)
where Me
is the mass spent on the planet surface.
The computation of the expense of mass (energy) for a perfect transfer of energy
(coefficient of efficiency = 1) versus the relative apparatus speed is presented in Figure 6.
Computations made in system coordinate connected with apparatus. The relativistic effect
(for Earth's observer) can change these results for high speed.
Note that in many ways the AB-Ramjet engine is better than the photon engine (which is
a dream of all space scientists). For example, if we want to reach the relative apparatus speed
of 0.1c, the AB-Ramjet can spend 20 times less energy than the photon engine. Moreover, the
AB-Ramjet engine can return spent energy (if it can transfer back self kinetic energy into
mass with high efficiency). That means a space ship (using AB-Ramjet engine) can travel into
space infinity time with stopping at planets (spending the mass for acceleration and return its
mass in braking). But the photon engine losses part of self mass in the photon beam and can
travel only limited time.
9) Force between engine plates is
E Sp
f
2
0
2
1
(18)
where 0 =8.8510 -12 is electrostatic coefficient [F/m], Sp is plate area [m2
]. For Sp = 1 m2
, E
=1000 V/m force f = - 4.42510 -6 N.
4. Ball (Central Charged Core) Discharge
The space apparatus or solar wind has high speed. This means the particles have a
trajectory closed to a hyperbolic curve in the AB-area of charge influence and most of them
will fly off into infinity. Only a proportion of them will travel through the ball. These
particles decrease in speed and can discharge the ball. However, their speed and kinetic
energy are very large because they are accelerated by the high voltage of the ball‘s electric
field (some tens or hundreds of MV). The necessary ball film (net) is very thin (measuring
only a few microns). The particles pierce through the ball. If their loss of speed is less than
their (apparatus) speed or the solar wind speed, their trajectory will be close to a hyperbolic
curve and they will fly into space. If their loss of speed is more than the solar wind speed,
their trajectory will be close to an ellipse, so they will return to the ball and, after many
New Concepts, Ideas and Innovations in Aerospace… 49
revolutions, they can discharge the ball if their perigee is less then the ball‘s radius. This
discharge may be compensated using special methods.
There are several possible methods for decreasing this discharge (Figure 2c-g): a) A ball
made of net; b), the central charge (core) has a cylindrical form (Figure 2f) without cover
butt-end; c) the plates increase the particles speed to hyperbolic speed and reflect the
returning particles. Note, the electric field does not depend on the form of the central charge
at far distances, but does depend on the value of the charge.
Let us estimate the discharging of the plates and the central charge (ball, core).
1) If the plate or ball has a net design, the particles will cross only the wires of plate.
Note, the maximum coefficient of light transparency c1 is the ratio of the area of the wires, Sw,
to the area of plate, Sp,
Sw S p
c /
1
(19)
2) The particles crossing the wire lose a part of their energy. This loss may be calculated
as a brake coefficient c2. The method of computation is described in the work [54].
The particle (proton) track in the matter can be computed in following way:
l = Rt /γ , (20)
where l is track distance of the particles [cm]; Rt = Rt (U) is magnitude (from a table) [g/cm2
];
γ is matter density [g/cm3
]. The magnitude of Rt depends on the kinetic energy (voltage) of
the particles. For protons the values of Rt are presented in Table 1.
Table 1. Magnitude of Rt as a function of accelerated voltage U = aE, volts
U, MV 100 200 300 400 500 600 700 1000 2000 3000 5000
Rt g/cm2
10 33.3 65.8 105 149 197 248 370 910 1463 2543
The proton energy is U = aE. For magnitudes a = 6 m, E = 108 V/m, proton energy U =
600106 V and ball cover density γ = 1.8 g/cm3
the proton track is l = 197/1.8 = 109 cm. The
loss of proton energy is proportional to the wire diameter or cover thickness. Consequently,
the particles brake coefficient is
l l
d
c
w
2
(21)
where dw is the diameter of the plate wires and is the thickness of the ball cover.
The full transparency coefficient c3 and energy of loss EL are
c3
c1
c2
, EL
c3E
(22)
where E is the energy of particle flow crossing the AB-Ramjet engine. Note, the energy loss
across the cylindrical core (charge located on the tube) is small because particles are moved
into the empty tube along its axis.
50 Alexander Bolonkin
The safe ball cover thickness may be estimated using the following method. The solar
wind proton energy is
2
2
p s
d
m V
E
(23)
For Vs = 400103
km/s the proton energy is Ed = 13.410 -17 J = 13.410 -17 0.6251019
eV = 840 eV.
If the loss of proton energy is proportional to the cover thickness, the maximum safe
cover thickness (which will not discharge the ball) will be
U aE
U
Ed V l
or
l
E U
s
d
,
( )
, max
max
(24)
For a = 6 m, E = 108 V/m, the required ball cover thickness is δmax = 1.53 micron. For a =
4, 10 m δmax = 1.22 and 1.73 microns, respectively.
This magnitude is less than the ball thickness required for the charge stress (see [54]) for
current cover matter. That way the net and cylindrical core is better then the thin-filmed
spherical ball.
For electrons, the thickness of half absorption may be calculated using equation [54]
0.095 ( ) [ / ], , [ ] 0.5
3/ 2 2
cm
R
aE g cm d
A
Z
R
r
r
(25)
Here Z is the nuclear charge of the ball matter; A is the mass number of the ball matter.
5. Initial expenditure eof electrical energy needed to charge the ball. The ball must be
charged with electrical energy of high voltage (millions of volts). Let us estimate the
minimum energy when the charged device has 100% efficiency. This energy equals the work
of moving of the ball charge to infinity, which may be computed using the equation
,
2
, , ,
2
2 2 3 2
k
a E W
k
a
C
k
a E
Q
C
Q W
(26)
where W is ball charge energy [J]; C is ball capacitance [F]; Q is ball charge [C]. The result of
this computation is presented in Figure 7. As can be seen this energy not huge since it is only
about 1 - 20 kWh for a ball radius of a = 5 m and the electrical intensity is 25 - 100 MV/m.
This energy may be restored through ball discharge by emitting the charge into space using a
sharp edge.
New Concepts, Ideas and Innovations in Aerospace… 51
Figure 7. Initial expenditure of electrical energy needed to charge the space apparatus, a = 1- 8 m,
electrical intensity is E = 25-100 MV/m and coefficient of efficiency = 1.
PROJECTS
Below the reader will find some examples which highlight the many benefits of the
proposed AB-Ramjet engines. Our parameters are not optimal. Our purpose is simply the
demonstration of the potential of AB-Ramjet propulsion.
Example 1. AB-Ramjets for Earth orbits
1. Brief description of Earth's upper atmosphere. The Earth's atmosphere consists of 79%
nitrogen, 20% oxygen, and 1% other gases. The atmosphere of the Earth may be divided into
several distinct layers. The first two are the troposphere (0 - 18 km) and the stratosphere (18 -
90 km). Above the stratosphere is the mesosphere and above that is the ionosphere (or
thermosphere), where many atoms are ionized (gain or lose electrons so they have a net
electrical charge). The Sun's ultra-violet radiation and solar wind ionize molecules of the top
atmosphere. The ionosphere is very thin, but it is where the aurora takes place, and it is also
responsible for absorbing the most energetic photons from the Sun and solar wind. The
concentration of ions (= electrons) at day and night time is shown in Figure 8.
The ionosphere is divided into the layers D, E, F1, F2. Layer D contains ions of N2 and
O2; the layers E, F1, F2 contain ions of O2 and O.
2. Estimations of AB-Ramjet engine data for low-Earth satellite orbits. Computations are
made for an apparatus (AB-Ramjet engine) having speed V0 = 8 km/s, a concentration of O2
ions = 105
ions/cm3
, and the electric intensity E = 108 V/m. The computation of the AB-radius
52 Alexander Bolonkin
is presented in Figure 9. An electrostatic collector gathers ions from a surrounding area of
more than10 km2
.
Figure 8. Concentration/cm3 of ions (= electrons) in the day timeand night time in the D, E, F1, and F2
layers of ionosphere.
Figure 9. AB-radius of charge (radius of efficiency, catch area, clamp area) versus the charge (ball)
radius for electric intensity E = 100 millions V/m, AB-Ramjet engine speed V0 = 8 km/s, O2
ion molar
mass n = 32, ion density N = 105
ions/cm3
. Equations are [4 - 6].
New Concepts, Ideas and Innovations in Aerospace… 53
Produced thrust and requested power are presented in figures 10, 11. As can be seen, the
thrust is significant enough to change the satellite's trajectory and increase the apparatus'
speed to a velocity close to that required for an interplanetary trip. The required energy may
be obtained from a solar battery.
Figure 10. AB-Ramjet engine thrust versus radius of charge (ball) and plate voltage U =1 - 5 V for V0 =
8 km/s, electric intensity E = 100 millions V/m, and ion density N = 105
ions/cm3
. Equation [9].
Figure 11. AB-Ramjet engine power versus radius of charge (ball) and plate voltage U = 1 - 5 V for V0
= 8 km/s, electric intensity E = 100 millions V/m, and ion density N = 105
ions/cm3
. Equation [11].
54 Alexander Bolonkin
Figure 12 shows the drag produced by the AB-Ramjet engine. Figure 13 shows the brake
electric energy. This energy may be used by apparatus devices or transferred to other space
apparatus.
Figure 12. AB-Ramjet engine drag versus radius of charge (ball) for V0 = 8 km/s, electric intensity E =
100 millions V/m, and ion density N = 105
ions/cm3
. Equation [9a].
Figure 13. AB-Ramjet engine power versus radius of charge (ball) for V0 = 8 km/s, electric intensity E
= 100 millions V/m, and ion density N = 105
ions/cm3
. Equation [11].
New Concepts, Ideas and Innovations in Aerospace… 55
The offered AB-engine may be used as an accelerator or brake for interplanetary space
apparatus. The method of acceleration is shown in Figure 14. In the acceleration regime in
region 7, the thruster of the AB-engine accelerates a probe and increases the apogee of the
elliptic trajectory. In the final trajectory, the probe is separated from the engine, gets a small
impulse, and flies away into space. When the probe returns from space flight, the sequence is
reversed and the AB-engine works as brake.
Figure14. Using the AB-engine as an accelerator and a brake for interplanetary flight. Notation: 1 -
Earth, 2 - Earth's atmosphere, 3 - accelerator trajectories, 4 - final trajectory of interplanetary probe, 7 -
region of acceleration and brake, 8 - solar light.
The particle mass flow and the electric current flow (computed by equation [8],[9]) are
shown in figs. 15, 16. The electric current is significantly large, creating a magnetic field
which helps to straighten the particle's trajectory.
Figure 15. Ion mass flow through the AB-engine. Equation [15].
56 Alexander Bolonkin
Figure 16. Electric current flow through the AB-engine. Equation [16].
The additional speed gained by the ions in AB-engine as computed by equation [7] via
the interplate voltage is shown in figure 17. Acceleration is produced in the thrust regime and
deceleration is produced in the brake regime.
Figure 17. The additional speed getting by ions when they move between engine plates.
New Concepts, Ideas and Innovations in Aerospace… 57
The size of the plates computed by equation [2b] is shown in Figure 18. As can be seen,
the size is very small and the plates can be located inside of the cylindrical charged core
(Figure 2f).
Figure 18. Size of AB-engine plates versus the ball radius. Equation [2b].
Example 2. Interplanetary AB-Ramjet
Brief information about the solar wind. The Sun emits plasma which is a continuous
outward flow (solar wind) of ionized solar gas throughout our solar system. The solar wind
contains about 90% protons and electrons and some quantities of ionized -particles and
gases. It attains speeds in the range of 300-750 km/s and has a flow density of 5107
- 5108
protons/ electrons/cm2
s. The observed speed rises systematically from low values (300-400
km/s) to high values (650-700 km/s) in 1 or 2 days and then returns to low values during the
next 3 to 5 days (Figure 19). Each of these high-speed streams tends to appear at
approximately 27-day intervals or to recur with the rotation period of the Sun. On days of
high Sun activity the solar wind speed reaches 1000 (and more) km/s and its flow density
is109
- 1010 protons/electrons/ cm2
s with 8 -70 particles per cm3
. The Sun has high activity
periods several days each year.
The pressure of the solar wind is very small. For full braking it is in the interval
2.510 -10 ÷ 6.310 -9 N/m2
. This value is doubled when the particles have full reflection. The
interstellar medium also has high-energy particles. Their density is about 1 particle/cm3
.
Estimation of main parameters of the AB-engine. Let us estimate the main parameters of
the AB-Ramjet engine for interplanetary apparatus. Interplanetary apparatus using a charged
58 Alexander Bolonkin
ball for solar wind drag was considered by the author in [54]. This work shows a great
potential for these apparatus.
Figure 19. Speed and density variations in solar wind. The speed is in km/s, the density is in
protons/cm3
.
The suggested AB-Ramjet engine (Figure 2) is different from the propulsion engine in
[54]. The AB-Ramjet has plates which can produce thrust, work as a generator of electrical
energy, create stronger drag, and improve the control of the value and direction of both the
drag and thrust. The central charge has a cylindrical form which dramatically decreases the
discharging of the central charged core. The proposed AB-Ramjet can simultaneously
produce useful drag (or thrust) and electric energy. It may seem astonishing, but an ABRamjet
located in the strong solar wind would be capable of achieving a speed between 400 -
750 km/s. If we install the wind engine in a conventional space ship, the engine will produce
sufficient energy and drag which would also useful if space ship moved in the wind direction.
The drag produced by solar wind is a useful thrust for moving from Earth to outer Earth orbit:
Saturn - Pluto. It may appear that this apparatus is lacking because it can only move away
from the Sun. However, that is not the case. The AB-ramjet apparatus can decrease the orbit
speed and the Sun's gravity will move it back to Earth orbit.
Estimates of the main parameters of the AB-ramjet interplanetary engine and apparatus
are given below. The equations used in computing the estimates are in theoretical section
[Eqs. 4 -6]. Figure 20 shows the AB-radius of the efficiency area (catch area, clamp area)
versus the charge radius of ball. Data used for computation: electric intensity E=100 millions
V/m, solar wind speed V0 = 400 km/s, solar wind density N = 10 protons/cm3
.
Mass and charge flow (electric current) through the AB-engine were computed using
equations [8] and [9]. Results are presented in figs. 21 and 22 for the following conditions:
electric intensity E=100 millions V/m, solar wind speed V0 = 400 km/s, solar wind density N
= 10 protons/cm3
. The flow mass is small (5 milligram/s), however the electric current is
large.
New Concepts, Ideas and Innovations in Aerospace… 59
Figure 20. Radius of efficiency (catch area, clamp area) versus the charge radius for electric intensity E
= 100 millions V/m, solar wind speed V0 = 400 km/s, solar wind density N = 10 protons/cm3
.
Equations are [4 - 6].
Figure 21. Flow of particles mass through the AB-Ramjet engine versus the charge radius for electric
intensity E = 100 millions V/m, solar wind speed V0 = 400 km/s, solar wind density N = 10
protons/cm3
.
60 Alexander Bolonkin
Figure 22. Flow electric currency through the AB-Ramjet engine versus the charge radius for electric
intensity E = 100 millions V/m, solar wind speed V0 = 400 km/s, solar wind density N = 10
protons/cm3
.
Figure 23. Maximal drag versus the charge radius for electric intensity E =100 millions V/m, solar
wind speed V0 = 400 km/s, solar wind density N = 10 protons/cm3
. Full reflection.
Figure 23 shows the maximal drag for full reflection versus the charge radius computed
via equation 9a for the conditions: electric intensity E = 100 millions V/m, solar wind speed
V0 = 400 km/s, solar wind density N = 10 protons/cm3
. As can be seen, the useful drag is
New Concepts, Ideas and Innovations in Aerospace… 61
sufficiently large and can produce significant acceleration for space apparatus. More detailed
computations for the conventional charge are presented in [54].
Thrust versus voltage between plates is shown in Figure 24 and the required energy for it
is presented in Figure 25. For a thrust of 0.2 N, the required power is 4.5 kW. We can
increase the voltage and obtain more thrust but the needed energy may not be acceptable for
the apparatus. If we change polarity of the plates, we get the same energy (Figure 26) from
apparatus braking, plus additional drag.
Figure 24. AB-Ramjet engine thrust versus radius of charge and plate voltage for V0 = 400 km/s and
flow density 10 protons/cm3
.
The maximum energy and half of full reflection drag will be obtained when the positive
value of (V0 - V) > 0 is close to zero. Here V0 is solar wind speed and V is apparatus speed
(positive direction from Sun). Using equation [7] (mV2
/2 = eU), for a wind speed V0 = 400
km/s, the calculation gives U = 835 V. This means for a highly charged ball, U = 0 produces
good reflection of the protons, near maximum drag, and zero positive electric energy. A U
slightly less than 835 V produces near maximum energy and a drag close to half of the
maximum drag (Figure23). The computation for this case is presented in Figure 26. The
power is significantly large and the engine may be used for both the apparatus and the
charging of the electrostatic collector (core).
Let us find the size of the electrostatic collector. The maximal size of the plate radius is
between the parameter Rh and the minimal radius of the hyperbolic trajectory. These
magnitudes are presented for the outermost particles in Figure 27. The computation shows a
particle flow that has maximum density in the plate center and small density in the plate ends.
We can determine a plate radius by the lower curve. For a charge (ball) radius of 10
meter, a plate radius of 20 meters is sufficient.
Let us estimate the discharging power for a radius of central charge of 10 meters. Let the
wire diameter of the engine plate net be 0.1 mm with a cell size of 1010 cm.
62 Alexander Bolonkin
Figure 25. Requested AB-Ramjet engine power for thrust versus radius of charge and plate voltage for
V0 = 400 km/s and flow density 10 protons/cm3
.
Figure 26. The maximum electric energy which can be obtained from the AB-Ramjet engine versus
charge radius. In this case the drag (half of full drag) accelerates the apparatus to far planets.
New Concepts, Ideas and Innovations in Aerospace… 63
Figure 27. The minimal radius and parameter Rh of hyperbolic trajectory of outermost particles.
The light transparency coefficient is c1 = 4(0.001)2
= 410-6
(Eq. [19]. The brake
coefficient of wire is c2 = 10-5
(Eq. [21]). The total transparency coefficient is c3 = c1c2 =
410 -11 (Eq. [22]). Loss of energy in the plate is L = c3IU = 410 -11450109
= 1.8 W. If we
take into consideration the cylindrical central charge and other support elements and increase
this value by 10, 100, 1000 times, the brake power (750 kW, Figure 26) will be enough for
the compensation this energy.
The maximum electric force between plates for a distance of 2 meters and a voltage of
1000 V is 0.14 N (eq. [18]). This means the support elements can be very light. The mass of
the two quadratic plates of size 2020 m having aluminum wires is 1.7 kg.
CONCLUSION
The primary research and computations of the suggested AB-engine show the numerous
possibilities and perspectives of the space AB-ramjet engines. The density of the charged
space particles is very small. But the proposed electrostatic collector can effectively gather
the particles from a huge surrounding area and accelerate or brake them, generating thrust or
braking on the order of several Newtons. The high speed solar wind allows simultaneously
obtainment of useful drag (thrust) and great electrical energy. The simplest electrostatic
gatherer accelerates a 100 kg probe up to a velocity of 100 km/s [54]. The probe offers flights
into Mars orbit of about 70 days, to Jupiter orbit in about 150 days, to Saturn orbit in about
250 days, to Uranus orbit in about 450 days, to Neptune orbit in about 650 days, and to Pluto
orbit in about 850 days.
The suggested electric gun is simple and can transfer energy (charge by electron beam)
over a long distance to other space apparatus.
64 Alexander Bolonkin
The author has developed the initial theory and the initial computations to show the
possibility of the offered concepts. He calls on scientists, engineers, space organizations, and
companies to research and develop the proposed perspective concepts.
REFERENCES
(Some of these works the reader finds in author side: http://Bolonkin.narod.ru/p65.htm
and http://Arxiv.org searth: Bolonkin)
[1] Bolonkin, A.A., (1965a), ―Theory of Flight Vehicles with Control Radial Force‖.
Collection Researches of Flight Dynamics, Mashinostroenie Publisher, Moscow, , pp.
79-118, 1965, (in Russian). Intern.Aerospace Abstract A66-23338#(Eng).
[2] Bolonkin A.A., (1965c), Optimization of Trajectories of Multistage Rockets. Collection
Researches of Flight Dynamics. Moscow, 1965, p. 20 -78 (in Russian). International
Aerospace Abstract A66-23337# (English).
[3] Bolonkin, A.A., (1982a), Installation for Open Electrostatic Field, Russian patent
application #3467270/21 116676, 9 July, 1982 (in Russian), Russian PTO.
[4] Bolonkin, A.A., (1982b), Radioisotope Propulsion. Russian patent application
#3467762/25 116952, 9 July 1982 (in Russian), Russian PTO.
[5] Bolonkin, A.A., (1982c), Radioisotope Electric Generator. Russian patent application
#3469511/25 116927. 9 July 1982 (in Russian), Russian PTO.
[6] Bolonkin, A.A., (1983a), Space Propulsion Using Solar Wing and Installation for It,
Russian patent application #3635955/23 126453, 19 August, 1983 (in Russian), Russian
PTO.
[7] Bolonkin, A.A., (1983b), Getting of Electric Energy from Space and Installation for It,
Russian patent application #3638699/25 126303, 19 August, 1983 (in Russian), Russian
PTO.
[8] Bolonkin, A.A., (1983c), Protection from Charged Particles in Space and Installation
for It, Russian patent application #3644168 136270, 23 September 1983, (in Russian),
Russian PTO.
[9] Bolonkin, A. A., (1983d), Method of Transformation of Plasma Energy in Electric
Current and Installation for It. Russian patent application #3647344 136681 of 27 July
1983 (in Russian), Russian PTO.
[10] Bolonkin, A. A., (1983e), Method of Propulsion using Radioisotope Energy and
Installation for It. of Plasma Energy in Electric Current and Installation for it. Russian
patent application #3601164/25 086973 of 6 June, 1983 (in Russian), Russian PTO.
[11] Bolonkin, A. A.,(1983f), Transformation of Energy of Rarefaction Plasma in Electric
Current and Installation for it. Russian patent application #3663911/25 159775, 23
November 1983 (in Russian), Russian PTO.
[12] Bolonkin, A. A., (1983g), Method of a Keeping of a Neutral Plasma and Installation for
it. Russian patent application #3600272/25 086993, 6 June 1983 (in Russian), Russian
PTO.
[13] Bolonkin, A.A.,(1983h), Radioisotope Electric Generator. Russian patent application
#3620051/25 108943, 13 July 1983 (in Russian), Russian PTO.
New Concepts, Ideas and Innovations in Aerospace… 65
[14] Bolonkin, A.A., (1983i), Method of Energy Transformation of Radioisotope Matter in
Electricity and Installation for it. Russian patent application #3647343/25 136692, 27
July 1983 (in Russian), Russian PTO.
[15] Bolonkin, A.A., (1983j), Method of stretching of thin film. Russian patent application
#3646689/10 138085, 28 September 1983 (in Russian), Russian PTO.
[16] Bolonkin, A.A., (1987), ―New Way of Thrust and Generation of Electrical Energy in
Space‖. Report ESTI, 1987, (Soviet Classified Projects).
[17] Bolonkin, A.A., (1990), ―Aviation, Motor and Space Designs‖, Collection Emerging
Technology in the Soviet Union, 1990, Delphic Ass., Inc., pp.32-80 (English).
[18] Bolonkin, A.A., (1991), The Development of Soviet Rocket Engines, 1991, Delphic
Ass.Inc.,122 p. Washington, (in English).
[19] Bolonkin, A.A., (1992a), ―A Space Motor Using Solar Wind Energy (Magnetic Particle
Sail)”. The World Space Congress, Washington, DC, USA, 28 Aug. - 5 Sept., 1992,
IAF-0615.
[20] Bolonkin, A.A., (1992b), “Space Electric Generator, run by Solar Wing‖. The World
Space Congress, Washington, DC, USA, 28 Aug. -5 Sept. 1992, IAF-92-0604.
[21] Bolonkin, A.A., (1992c), “Simple Space Nuclear Reactor Motors and Electric
Generators Running on Radioactive Substances‖, The World Space Congress,
Washington, DC, USA, 28 Aug. - 5 Sept., 1992, IAF-92-0573.
[22] Bolonkin, A.A. (1994), ―The Simplest Space Electric Generator and Motor with
Control Energy and Thrust”, 45th International Astronautical Congress, Jerusalem,
Israel, 9-14 Oct., 1994, IAF-94-R.1.368.
[23] Bolonkin, A.A., (2002a), “Non-Rocket Space Rope Launcher for People‖, IAC-02-
V.P.06, 53rd International Astronautical Congress, The World Space Congress - 2002,
10-19 Oct 2002, Houston, Texas, USA.
[24] Bolonkin, A.A,(2002b), ―Non-Rocket Missile Rope Launcher‖, IAC-02-IAA.S.P.14,
53rd International Astronautical Congress, The World Space Congress - 2002, 10-19
Oct 2002, Houston, Texas, USA.
[25] Bolonkin, A.A.,(2002c), ―Inexpensive Cable Space Launcher of High Capability‖, IAC02-V.P.07,
53rd International Astronautical Congress, The World Space Congress -
2002, 10-19 Oct 2002, Houston, Texas, USA.
[26] Bolonkin, A.A.,(2002d), ―Hypersonic Launch System of Capability up 500 tons per day
and Delivery Cost $1 per Lb‖. IAC-02-S.P.15, 53rd International Astronautical
Congress, The World Space Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[27] Bolonkin, A.A.,(2002e), ―Employment Asteroids for Movement of Space Ship and
Probes‖. IAC-02-S.6.04, 53rd International Astronautical Congress, The World Space
Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[28] Bolonkin, A.A., (2002f), ―Optimal Inflatable Space Towers of High Height‖. COSPAR02
C1.1-0035-02, 34th Scientific Assembly of the Committee on Space Research
(COSPAR), The World Space Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[29] Bolonkin, A.A., (2002g), ―Non-Rocket Earth-Moon Transport System‖, COSPAR-02
B0.3-F3.3-0032-02, 02-A-02226, 34th Scientific Assembly of the Committee on Space
Research (COSPAR), The World Space Congress - 2002, 10-19 Oct 2002, Houston,
Texas, USA.
66 Alexander Bolonkin
[30] Bolonkin, A. A.,(2002h) ―Non-Rocket Earth-Mars Transport System‖, COSPAR-02
B0.4-C3.4-0036-02, 34th Scientific Assembly of the Committee on Space Research
(COSPAR), The World Space Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[31] Bolonkin, A.A.,(2002i). ―Transport System for Delivery Tourists at Altitude 140 km‖.
IAC-02-IAA.1.3.03, 53rd International Astronautical Congress, The World Space
Congress - 2002, 10-19 Oct. 2002, Houston, Texas, USA.
[32] Bolonkin, A.A., (2002j), ‖Hypersonic Gas-Rocket Launch System.‖ AIAA-2002-3927,
38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 7-10 July
2002. Indianapolis, IN, USA.
[33] Bolonkin, A.A., (2003a), ―Air Cable Transport‖, Journal of Aircraft, Vol. 40, No. 2,
March-April 2003.
[34] Bolonkin, A.A., (2003b), ―Optimal Inflatable Space Towers with 3-100 km Height‖,
JBIS, Vol. 56, No 3/4, pp. 87-97, 2003.
[35] Bolonkin, A.A.,(2003c), ―Asteroids as Propulsion Systems of Space Ships‖, JBIS, Vol.
56, No 3/4, pp. 97-107, 2003.
[36] Bolonkin A.A., (2003d), ―Non-Rocket Transportation System for Space Travel‖, JBIS,
Vol. 56, No 7/8, pp. 231-249, 2003.
[37] Bolonkin A.A., (2003e), ―Hypersonic Space Launcher of High Capability‖, Actual
problems of aviation and aerospace systems, Kazan, No. 1(15), Vol. 8, 2003, pp. 45-58.
[38] Bolonkin A.A., (2003f), ―Centrifugal Keeper for Space Stations and Satellites‖, JBIS,
Vol. 56, No 9/10, pp. 314-327, 2003.
[39] Bolonkin A.A., (2003g), ―Non-Rocket Earth-Moon Transport System‖, Advances in
Space Research, Vol. 31/11, pp. 2485-2490, 2003, Elsevier.
[40] Bolonkin A.A., (2003h), ―Earth Accelerator for Space Ships and Missiles‖. JBIS, Vol.
56, No. 11/12, 2003, pp. 394-404.
[41] Bolonkin A.A., (2003i), ―Air Cable Transport and Bridges‖, TN 7567, International Air
and Space Symposium - The Next 100 Years, 14-17 July 2003, Dayton, Ohio, USA.
[42] Bolonkin, A.A., (2003j), ―Air Cable Transport System‖, Journal of Aircraft, Vol. 40,
No. 2, March-April 2003, pp. 265-269.
[43] Bolonkin A.A.,(2004a), ―Kinetic Space Towers and Launchers ‗, JBIS, Vol. 57, No 1/2,
pp. 33-39, 2004.
[44] Bolonkin A.A.,(2004b), ―Optimal trajectory of air vehicles‖, Aircraft Engineering and
Space Technology, Vol. 76, No. 2, 2004, pp. 193-214.
[45] Bolonkin A.A., (2004c), ―Long Distance Transfer of Mechanical Energy‖, International
Energy Conversion Engineering Conference at Providence RI, Aug. 16-19, 2004,
AIAA-2004-5660.
[46] Bolonkin, A.A., (2004d), ―Light Multi-Reflex Engine‖, Journal JBIS, Vol. 57, No 9/10,
pp. 353-359, 2004.
[47] Bolonkin, A.A., (2004e), ―Kinetic Space Towers and Launchers‖, Journal JBIS, Vol.
57, No 1/2, pp. 33-39, 2004.
[48] Bolonkin, A.A., (2004f), ―Optimal trajectory of air and space vehicles‖, AEAT, No 2,
pp. 193-214, 2004.
[49] Bolonkin, A.A.,(2004g), ―Hypersonic Gas-Rocket Launcher of High Capacity‖, Journal
JBIS, Vol. 57, No 5/6, pp. 167-172, 2004.
New Concepts, Ideas and Innovations in Aerospace… 67
[50] Bolonkin, A.A., (2004h), ―High Efficiency Transfer of Mechanical Energy‖.
International Energy Conversion Engineering Conference at Providence RI, USA. 16-
19 August, 2004, AIAA-2004-5660.
[51] Bolonkin, A.A., (2004i), ―Multi-Reflex Propulsion System for Space and Air
Vehicles‖, JBIS, Vol. 57, No 11/12, 2004, pp. 379-390.
[52] Bolonkin A.A.,(2005a) ―High Speed Catapult Aviation‖, AIAA-2005-6221,
Atmospheric Flight Mechanic Conference - 2005, 15-18 August, 2005, USA.
[53] Bolonkin A.A., (2005a), Electrostatic Solar Wind Propulsion System, AIAA-2005-
3653. 41-st Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[54] Bolonkin A.A., (2005b), Electrostatic Utilization of Asteroids for Space Flight, AIAA2005-4032.
41 Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[55] Bolonkin A.A., (2005c), Kinetic Anti-Gravitator, AIAA-2005-4504. 41-st Propulsion
Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[56] Bolonkin A.A., (2005d), Sling Rotary Space Launcher, AIAA-2005-4035. 41-st
Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[57] Bolonkin A.A., (2005e), Radioisotope Space Sail and Electric Generator, AIAA-2005-
4225. 41-st Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[58] Bolonkin A.A., (2005f), Guided Solar Sail and Electric Generator, AIAA-2005-3857.
41-st Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[59] Bolonkin A.A., (2005g), Problems of Electrostatic Levitation and Artificial Gravity,
AIAA-2005-4465. 41 Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[60] Bolonkin A.A., (2006), Non-Rocket Space Launch and Flight, Elsevier, London, pp.
488.
New Concepts, Ideas and Innovations in Aerospace…
Attachment to Part A, Ch. 2. Possible form of space ships
70 Alexander Bolonkin
New Concepts, Ideas and Innovations in Aerospace… 71
Chapter 3
BEAM SPACE PROPULSION
ABSTRACT
In this Chapter author offers a revolutionary method - non-rocket transfer of energy
and thrust into Space with distance of millions kilometers. The author has developed
theory and made the computations. The method is more efficient than transmission of
energy by high-frequency waves. The method may be used for space launch and for
acceleration the spaceship and probes for very high speeds, up to relativistic speed by
current technology. Research also contains prospective projects which illustrate the
possibilities of the suggested method.
Keywords: space transfer of energy, space transfer of thrust, transferor of matter,
transfer of impulse (momentum), interplanetary flight, interstellar flight.
INTRODUCTION
Transportation of energy, matter, or impulse is very important for long period space trips
especially for lengthy distance voyages. The spaceship crew or astronauts on planets can need
additional energy or ship thrust. Most people think that is impossible to transfer energy a long
distance in outer space except electromagnetic waves. Unfortunately, electromagnetic waves
have a big divergence and cannot be used at a long distance (millions of kilometers) transfer.
However, the space vacuum is very good medium for offered method and special transfer
of energy and momentum.
Brief history. About 40 years ago scientists received plasma flow having speed up 1000
km/s, power 10 kW, mass consumption 0.1 g/s, electric current up million amperes.
However, the application of plasma beam into space needs a series of inventions,
innovations and researches. In particular, they include methods of decreasing the plasma
divergence, discharging, dispersion of velocity, collection the plasma beam in space at long
Presented as Bolonkin‘s paper AIAA-2006-7492 to Conference "Space-2006", 19-21 September, 2006, San-Jose,
CA, USA.
72 Alexander Bolonkin
distance from source, conversion of the beam energy into electricity and other types of
energy, conversion of plasma impulse (momentum) in space apparatus thrust, conversion of
plasma into matter, control, etc.
The author started this research more then forty years ago [1]. The solutions of the main
noted problems and innovations are suggested by author in early (1982-1983) patent
applications [2] - [12] (see also further development in [13]-[31]) and given article. In
particularly, the main innovations are:
1. Using neutral plasma (not charged beam);
2. Using ultra-cool plasma or particle beam in conventional temperature;
3. Control electrostatic collector which separates and collects the ions at spaceship;
4. Control electrostatic generator which convert the ion kinetic energy into electricity;
5. Control electrostatic ramjet propulsion;
6. Special control electrostatic mirror-reflector;
7. Recombination photon engine;
8. Recombination thermo-reactor.
9. Research is made for conventional and relativistic particle speeds.
About 20 years ago the scientists received the ultra-cold plasma having the ion
temperature lower then 110-3 oK. Velocity dispersion was 10-4
10-6
, beam divergence for
conventional temperature was 10-3
radian.
If plasma accelerator is designed special for getting the ultra-cold plasma, its temperature
may be appreciably decreased. There is no big problem in getting of cold ions from solid
electrodes or cold electrons from solid points where molecular speed is small.
DESCRIPTION OF INNOVATION
Innovative installation for transfer energy and impulse includes (Figure 1): the ultra-cold
plasma injector, electrostatic collector, electrostatic electro-generator-thruster-reflector, and
space apparatus. The plasma injector creates and accelerates the ultra-cold low density
plasma.
The Installation works the following way: the injector-accelerator forms and injects the
cold neutral plasma beam with high speed in spaceship direction. When the beam reaches the
ship, the electrostatic collector of spaceship collects and separates the beam ions from large
area and passes them through the engine-electric generator or reflects them by electrostatic
mirror. If we want to receive the thrust in the near beam direction (90o
) and electric energy,
the engine works as thruster (accelerator of spaceship and braker of beam) in beam direction
and electric generator. If we want to get thrust in opposed beam direction, the space engine
must accelerate the beam ions and spend energy. If we want to have maximum thrust in beam
direction, the engine works as full electrostatic mirror and produces double thrust in the beam
direction (full reflection of beam back to injector). The engine does not spend energy for full
reflection.
The thrust is controlled by the electric voltage between engine nets [19], the thrust
direction is controlled by the engine nets angle to beam direction. Note, the trust can brake the
New Concepts, Ideas and Innovations in Aerospace… 73
ship (decrease the tangential ship speed) and far ship (located out of Earth orbit) can return to
the Earth by Sun gravity.
Note also, the Earth atmosphere absorbs and scatters the plasma beam and the beam
injector must be located on Earth space mast or tower (up 40 60 km, see [20, 21]) or the
Moon. Only high energy beam can break through atmosphere with small divergence. The
advantage: the injector has a reflector and when the ship locates not far from the injector the
beam will be reflected a lot of times and thrust increases in thousand times at start (Figure 2)
(see same situation in [22]).
The proposed engine may be also used as AB-ramjet engine [19], utilizing the Solar wind
or interstellar particles.
Figure 1. Long distance space transfer of electric energy, matter, and momentum (thrust). Notations
are: 1 - injector-accelerator of neutral ultra-cold plasma (ions and electrons), 2 - plasma beam, 3 - space
ship or planetary team, 4 - electrostatic ions collector (or magnetic collector), 5 - braking electric nets
(electrostatic electro-generator-thruster-reflector), 6 - thrust.
Figure 2. Multi-reflection start of the spaceship having proposed engine. Notations are: 1 - injectoraccelerator
of cold ions or plasma, 2 , 3 - electrostatic reflectors, 4 - space ship, 5 - plasma beam, 6 - the
thrust.
The electrostatic collector and electrostatic generator-thruster-reflector proposed and
described in [19]. The main parts are presented below.
A Primary Ramjet propulsion engine is shown in Figure 1 Chapter 2. Such an engine can
work in charged environment. For example, the surrounding region of space medium contains
positive charge particles (protons, ions). The engine has two plates 1, 2, and a source of
electric voltage and energy (storage) 3. The plates are made from a thin dielectric film
covered by a conducting layer. The plates may be a net. The source can create an electric
voltage U and electric field (electric intensity E) between the plates. One also can collect the
electric energy from plate as an accumulator.
The engine works in the following way. Apparatus are moving (in left direction) with
velocity V (or particles 4 are moving in right direction). If voltage U is applied to the plates, it
74 Alexander Bolonkin
is well-known that main electric field is only between plates. If the particles are charged
positive (protons, positive ions) and the first and second plate are charged positive and
negative, respectively, then the particles are accelerated between the plates and achieve the
additional velocity v > 0. The total velocity will be V+v behind the engine (Figure 1a, Ch. 2).
This means that the apparatus will have thrust T > 0 and spend electric energy W < 0 (bias,
displacement current). If the voltage U = 0, then v = 0, T = 0, and W = 0 (Figure 1b, Ch.2).
If the first and second plates are charged negative and positive, respectively, the voltage
changes sign. Assume the velocity v is satisfying -V < v < 0. Thus the particles will be braked
and the engine (apparatus) will have drag and will also be braked. The engine transfers braked
vehicle energy into electric (bias, displacement) current. That energy can be collected and
used. Note that velocity v cannot equal -V. If v were equal to -V, that would mean that the
apparatus collected positive particles, accumulated a big positive charge and then repelled the
positive charged particles.
If the voltage is high enough, the brake is the highest (Figure 1d, Ch.2). Maximum
braking is achieved when v = -2V (T < 0, W = 0). Note, the v cannot be more then -2V,
because it is full reflected speed.
AB-Ramjet engine. The suggested Ramjet is different from the primary ramjet. The
suggested ramjet has specific electrostatic collector 5 (Figure 2a,c,d,e,f,g, Ch. 2). Other
authors have outline the idea of space matter collection, but they did not describe and not
research the principal design of collector. Really, for charging of collector we must move
away from apparatus the charges. The charged collector attracts the same amount of the
charged particles (charged protons, ions, electrons) from space medium. They discharged
collector, work will be idle. That cannot be useful.
The electrostatic collector cannot adsorb matter (as offered some inventors) because it
can adsorb ONLY opposed charges particles, which will be discharged the initial charge of
collector. Physic law of conservation of charges does not allow to change charges of particles.
The suggested collector and ramjet engine have a special design (thin film, net, special
form of charge collector, particle accelerator). The collector/engine passes the charged
particles ACROSS (through) the installation and changes their energy (speed), deflecting and
focusing them. That is why we refer to this engine as the AB-Ramjet engine. It can create
thrust or drag, extract energy from the kinetic energy of particles or convert the apparatus'
kinetic energy into electric energy, and deflect and focus the particle beam. The collector
creates a local environment in space because it deletes (repeals) the same charged particles
(electrons) from apparatus and allows the Ramjet to work when the apparatus speed is close
to zero. The author developed the theory of the electrostatic collector and published it in [26].
The conventional electric engine cannot work in usual plasma without the main part of the
AB-engine - the special pervious electrostatic collector.
The plates of the suggested engine are different from the primary engine. They have
concentric partitions which create additional radial electric fields (electric intensity) (Figure
2b, Ch.2). They straighten, deflect and focus the particle beams and improve the efficiency
coefficient of the engine.
The central charge can have a different form (core) and design (Figure 2 c,d,e,f,g,h,
Ch.2). It may be:
(1) a sphere (Figure 2c, Ch. 2) having a thin cover of plastic film and a very thin (some
nanometers) conducting layer (aluminum), with the concentric spheres inserted one
into the other (Figure2d, Ch. 2),
New Concepts, Ideas and Innovations in Aerospace… 75
(2) a net formed from thin wires (Figure 2e, Ch. 2);
(3) a cylinder (without butt-end)(Figure 2f, Ch. 2); or
(4) a plate (Figure 2g, Ch. 2).
The design is chosen to produce minimum energy loss (maximum particle transparency -
see section "Theory"). The safety (from discharging, emission of electrons) electric intensity
in a vacuum is 108 V/m for an outer conducting layer and negative charge. The electric
intensity is more for an inside conducting layer and thousands of times more for positive
charge.
The engine plates are attracted one to the other (see theoretical section). They can have
various designs (Figure 3a - 3d, Ch. 2). In the rotating film or net design (Figure 3a, Ch. 2),
the centrifugal force prevents contact between the plates. In the inflatable design (Figure 3b,
Ch. 2), the low pressure gas prevents plate contact. A third design has (inflatable) rods
supporting the film or net (Figure 3c, Ch. 2). The fourth design is an inflatable toroid which
supports the distance between plates or nets (Figure 3d, Ch.2).
Note, the AB-ramjet engine can work using the neutral plasma. The ions will be
accelerated or braked, the electrons will be conversely braked or accelerated. But the mass of
the electrons is less then the mass of ions in thousands times and AB-engine will produce
same thrust or drag.
Plasma accelerator. The simplest linear plasma accelerator (principle scheme of linear
particle accelerator) for plasma beam is presented in Figure 4, Ch. 2. The design is a long
tube (up 10 m) which creates a strong electric field along the tube axis (100 MV/m and
more). The accelerator consists of the tube with electrical isolated cylindrical electrodes, ion
source, and voltage multiplier. The accelerator increases speed of ions, but in end of tube into
ion beam the electrons are injected. This plasma accelerator can accelerate charged particles
up 1000 MeV. Electrostatic lens and special conditions allow the creation of a focusing and
self-focusing beam which can transfer the charge and energy long distances into space. The
engine can be charged from a satellite, a spaceship, the Moon, or a top atmosphere station
(space tower [19, 28]). The beam may also be used as a particle beam weapon.
Approximately ten years ago, the conventional linear pipe accelerated protons up to 40
MeV with a beam divergence of 10-3
radian. However, acceleration of the multi-charged
heavy ions may result in significantly more energy.
At present, the energy gradients as steep as 200 GeV/m have been achieved over
millimeter-scale distances using laser pulsers. Gradients approaching 1 GeV/m are being
produced on the multi-centimeter-scale with electron-beam systems, in contrast to a limit of
about 0.1 GeV/m for radio-frequency acceleration alone. Existing electron accelerators such
as SLAC could use electron-beam afterburners to
increase the intensity of their particle beams. Electron systems in general can provide tightly
collimated, reliable beams while laser systems may offer more power and compactness.
The cool plazma beam carries three types of energy: kinetic energy of particles,
ionization, and dissosiation energy of ions and moleculs. That carry also particle mass and
momentum. The AB-Ramjet engine (discribed over) can utilise only kinetic energy of plasma
particles and momentum. The particles are braked and produce an electric current and thrust
or reflected and produce only thrust in the beam direction. If we want to collect a plasma
matter and to utilize also the ionization energy of plasma (or space invironment) ions and
76 Alexander Bolonkin
dissociation energy of plasma molecules we must use the modified AB-Ramjet engine
discribed below (Figure 3).
The modified AB-engine has magnetic collector (option), three nets (two last nets may be
films), and issue voltage (that also may be an electric load). The voltage, U, must be enough
for full braking of charged particles. The first two nets brake the electrons and precipitate
(collect) the electrons on the film 2 (Figure 3). The last couple of film (2, 3 in Figure3) brakes
and collects the ions. The first couple of nets accelerate the ions that is way the voltage
between them must be double.
Figure 3. AB-engine which collected matter of plasma beam, kinetic energy of particles, energy
ionization and dissociation. Notations: 1 - magnetic collector; 2 - 4 - plates (films, nets) of engine; 5 -
electric load; 6 - particles of plasma; 7 - radiation. U - voltage between plates (nets).
The collected ions and electrons have the ionized and dissociation energy. This energy is
significantly (up 20 - 150 times) more powerful then chemical energy of rocket fuel (see
Table 1) but significantly less then kinetic energy of particles (ions) equal U (in eV) (U may
be millions volts). But that may be used by ship. The ionization energy conventionally pick
out in photons (light, radiation) which easy are converted in a heat (in closed vessel), the
dissociation energy conventionally pick out in heat.
The light energy may be used in the photon engine as thrust (Figure 4a) or in a new
power laser (Figure 4b). The heat energy may be utilized conventional way (Figure 4c). The
offered new power laser (Figure 4b) works the following way. The ultra-cool rare plasma
with short period of life time located into cylinder. If we press it (decrease density of plasma)
the electrons and ions will connect and produce photons of very closed energy (laser beam). If
we compress very quickly by explosion the power of beam will be high. The power is only
limited amount of plasma energy.
After recombination ions and electrons we receive the conventional matter. This matter
may be used as nuclear fuel (in thermonuclear reactor), medicine, food, drink, oxidizer for
breathing, etc.
New Concepts, Ideas and Innovations in Aerospace… 77
Figure 4. Conversion of ionization energy into radiation and heat. a - photon engine; b - power laser
(light beamer); c - heater. Notations: 1 - recombination reactor; 2 - mirror; 3 - radiation (light) beam; 5 -
piston; 6 - volume filled by cold rare plasma; 7 - beam; 8 - plasma; 9 - heat exchanger; 10 - enter and
exit of hear carrier; 11 - heat carrier.
TRANSFER THEORY OF THE HIGH SPEED NEUTRAL ULTRA-COLD
PLASMA AND PARTICLES
Below are the main equations and computations of neutral ultra-cold plasma beam having
velocity up to relativistic speed. These equations received from conventional mechanics and
relativistic theory.
Note a ratio
c
V
c
V S
, S
(1)
where V is plasma beam speed, m/s; c = 3108
is light speed, m/s; Vs
is projection of a ship
speed in beam direction.
1. Relative relativistic time,
t
, for observer moving together with beam is
2
1
t
t
t
(2)
where t' is time for observer moving together with beam (system coordinate connected with
beam)[s], t is time for Earth's observer [s]. Computation of Eq. (2) is presented in Figure 5.
The beam time decreases for relativistic speed. That means the beam divergence is also
decreased and beam energy may be passed for long distance.
78 Alexander Bolonkin
Figure 5. Beam relative time versus beam relative speed for high relativistic beam speed.
2. The power spent for acceleration plasma beam in Earth for efficiency = 1 (kinetic
power of particle beam) is
2
, or for 1
2 1
2
0
2
2 2
0 M V
P
M c
PB B
[W/s] (3)
where M0 is mass flow of beam, kg/s in Earth system of coordinate.
The computations of Eq. (3) for the intervals (0 0.1)c and (0 0.95)c are presented in
Figures 6, 6a.
The relativistic speed needs very high power in any method because the relativistic beam
requires this energy.
3. The power Pi of dissociation and single ionization of one nucleon is
1.6 10 [ ] or [eV]
1 9 0 0
i
p
i i
p
i
e
m n
M
e J P
m n
M
P
(4)
where mp=1.6710-27 kg is mass of proton, n is number of nucleon in nucleus, ei
is energy of
dissociation, ionization, or molecular breakup respectively. The energy of the first ionization
(ion lost one electron) approximately equals from 2 to 14 eV. Magnitudes of this energy for
some molecules and ions are in Table No.1.
New Concepts, Ideas and Innovations in Aerospace… 79
Table 1. Energy ionization, dissociation, and molecular breakup of some molecules
and ions in eV
Molecular breakup H2O H2 + O 2 eV CO2 C+O2 0.093 eV
Dissociation H2 H+H 4.48 eV O2 O + O 5.1 eV
Ionization HH
+ 13.6 eV H2
H2
2.65 eV
Ionization O2
O2
6.7 eV
Figure 6. Power for the beam acceleration via beam flow mass and relative beam speed for interval.
(0 0.1)c
Figure 6a. Power for the beam acceleration via beam flow mass and relative beam speed for interval
(0 0.95)c.
80 Alexander Bolonkin
If speed is relativistic, this energy is small in comparison with kinetic energy of beam.
For interplanetary speed (VS = 8 -15 km/s) the energy of ionization reaches 15 - 50% from
kinetic energy of beam. That decreases the coefficient of efficiency launch installation. If we
used the heavy ions or a charged matter, the ionization energy decreases but voltage
increases. For interplanetary vehicles it is not important because required voltage for low
speed are small (U 5 20 V).
Figure 7 shows the required energy for different case
Figure 7. Power of ionization versus mass flow and ionization potencial (Eq. (4)).
4. The maximal thrust (drag) from the full reflected one charged plasma beam, for
Earth's observer and relativistic speed and non-relativistic speed may be estimated by
following equations:
for 1, 1, the thrust is 2 ( )
,
1
2
, or for 1 the thrust is
1
2 ( )
2 ( )
max 0
2
0
2
0
max
S S
S nax
S
S
T M V V
M c
T
M c
T M V V
(5)
Here M is calculated mass of a moving relativistic particle flow, kg/s; M0 is mass of the
particle flow measured by Earth's observer, kg/s.
Note: If the space ship move along the beam in same direction, the thrust is decreased
(sign is "-"); if that moves in opposed direction, the drag is increased (sing is "+"). This drag
(thrust) is not requested the ship propulsion energy.
Result of computation for intervals (0 0.1)c, (0 0.95)c, VS = 0 are presented in
Figure 8, 8a.
New Concepts, Ideas and Innovations in Aerospace… 81
Figure 8. Maximum thrust (drag) is produced by beam in space ship for VS = 0 and the interval
(0 ÷ 0.1)c.
Figure 8a. Maximum thrust (drag) is produced by beam in space ship for VS = 0 and interval
(0 ÷ 0.95)c.
5. The divergence of beam is a very important magnitude. If divergence is small, we can
pass our energy in long distance S:
82 Alexander Bolonkin
S c t
S
D
S D
c
u
Vt
ut
D
, ,
1
2
(6)
where u is maximal radial speed, m/s; D is maximal radial distance (radius of plasma beam),
m;
D
is relative divergence (angle of divergence,
2D 2D)
radians); t is time of beam
moving, s.
The computation of Eq. (6) is shown in Figure 9. We need in small u (ultra-cold plasma)
for decreasing of divergence as small as possible (u = 0.01 - 1 m/s). In this case we can
transfer energy in the large distance and accelerate a ship for relativistic speed. The plasma is
mixture of ions and electrons. If it is low-density, it can exist a long time. The cold plasma
can be emitted from solid electrodes.
Note: Equations (2),(6) shows when V c, then t' 0 and deviation D 0. That means
the deviation can be small as we want but we need a big power for it.
The corresponding temperature is
,
2
ik
mu Tc
(7)
where m is mass of molecule (ion) [kg]; m = mpn , here mp=1.6710 -27 is mass of proton, n is
number of nucleons into nucleus; i = 3 for single ion (for example O
+
), i = 5 for double
molecule (for example
O2
), i = 6 for multi-molecular ions, k = 1.3910 -23 is Boltzmann
constant.
For u = 0.1 1 m/s the temperature is about 10 -3 oK, the relative divergence is 10 -9
.
Figure 9. Radius of beam divergence via distance and ratio V/c.
New Concepts, Ideas and Innovations in Aerospace… 83
6. Accelerate voltage is
2
2 2 2
2 2 1
nc
q
m
q
mV U
p
(8)
where q = 1.610-19 C is electron (ion) charge. The computations are presented in Figure 10,
10a. The need voltage may be reduced in Z times if the ion has Z charges (delete Z electrons
from ion).
Figure 10. Accelerated voltage versus the coventinal beam speed and number of nucleons.
Figure 10a. Accelerated voltage versus a relativistic speed ratio V/c and number of nucleons.
84 Alexander Bolonkin
7. The speed Vs and distance of space ship S can be computed by conventional method
(Earth's observer):
S
S
S M
T
a
a
V
S
at V at S
,
2
,
2
,
2 2
a is ship acceleration, m/s2
. Ms
is ship mass, kg, VS is ship speed measured by Earth's
observer, m/s.
Figure 11. Ship speed for 100-days flight versus distance and ship acceleration.
8. Relative beam speed for a ship observer is
S
S
BS
1
(9)
where , S is relative speed of beam and space ship respectively measured by Earth's
observer. The sign " -" is used for same direction of speeds.
9. Loss energy of the beam in the Earth atmosphere may be estimated by the following
way:
U
m
m
R
m
m
R
R U
H h p h p
t
p
t
t
,
( )
100 ( ) ( )
00
(10)
where H0 = Pa/ = 104
/1.225 = 8163 m is thickness (height) of Earth atmosphere having
constant density = 1.225 kg/m3
, Pa = 104
kg/m2
is the atmospheric pressure;
(h)
is
New Concepts, Ideas and Innovations in Aerospace… 85
relative atmosphere density;
p(h)
is relative atmosphere pressure; Rt
is particle track in
atmosphere [cm]; m is mass of particle, kg; h is altitude, m; U is beam energy, MeV; o =
0,001225 g/cm3
is atmosphere density; 100 is transfer coefficient meter into cm. Magnitudes
Rt
, (h), p(h)
for proton are given below in Table 2, 3.
Table 2. Value Rt [g/cm2
] versus energy of proton in MeV, [32], p. 953
U MeV 0.1 1 10 50 100 200 300 400 500
Rt g/cm2
110-4
1.0910-2
0,9910-1 2.56 8.835 29.64 58.08 93.73 133.3
U 600 700 800 1000 2000 3000 5000 7000 10,000
Rt 176 222 270 370 910 1363 2543 3583 5081
Table 3. Standard Earth atmosphere, [33], p. 261
h km 0 5 10 20 40 60 100
(h)
1 0.661 0.338 0.072 3.2710-3
2.7110-4
4.4110-7 p(h)
1 0.533 0.261 0.054 2.9210-3
8.3510-4
3.2010-7
Results of computation Eq. (10) are presented in Figure 12, 12a, 12b.
Figure 12. Relative energy loss of the proton particle beam via a tower altitude in Earth atmosphere.
Accelerate voltage U are in millions volts.
86 Alexander Bolonkin
Figure 12a. Relative energy loss of the proton particle beam via a tower altitude in Earth atmosphere.
Accelerate voltage U are in millions volts. Angles in curve are result of the linearization
data of Table 2, 3.
Figure 12b. Relative energy loss of the particle beam via the tower altitude in Earth atmosphere and
number n of nucleons in nucleus. Accelerate voltage U in millions volts.
New Concepts, Ideas and Innovations in Aerospace… 87
Evidently, only high energy particle beam break up the Earth atmosphere. There is no
problem if the particle beam starts from a space tower [20], [25] of 40 80 km altitude or
from the Moon.
Last formula in (10) allows recalculation by the particle track for any atom. For example,
we want tocalculate the particle track for oxidizer particle having m = 16mp and energy 8,000
MeV. We take the Rt from Table 2 for U = 8,000/16 = 500 MeV and multiple by 16. Result Rt
= 13316=2128. The particle track Tr = Rt
/o = 2128/0.001225 =1737142 cm = 17.4 km in the
air having density 1.225 kg/m3
. That is enough to break the Earth's atmosphere of the constant
density 8.163 km, but the loss of energy will be = 8.163/17.4 = 0.47 (47%). The divergence
may also be increased by atmosphere. Loss and divergence may be improved is the beam
station is located on a mountain or special tower having the height about 40 60 km.
9. Multi-reflex launch and landing (Figure2). In a starting or braking period the thrust
(braking) can be increasing if we use the multi-reflect method developed in [26]. Multi-reflect
in launching does not increased the installation power (thrust is increased by increasing of
efficiency), multi-reflex in braking converts the apparatus kinetic energy into the electric
energy which can be utilized by apparatus or operated station. The theory of multi-reflection
is described below (see also [26]).
Change in beam power. The beam power will be reduced if one (or both) reflector is
moved, because the beam speed changes. The total relative loss, q, of the beam energy in one
double cycle (when the beam is moved to the reflector and back) is
q = (1–2γ)(1–2ξ)(1±2v)ς , q > 0 , (11)
where v is the loss (useful work) through relative mirror (lens) movement, v = VS/V, VS is the
relative speed of the electrostatic mirrors (space apparatus)[m/s], V = is the speed of the beam
(in system of coordinates connected with an power operating station). We take the ―+‖ when
the distance is reduces (braking) and take ―– ― when the distance is increased (as in launching,
a useful work for beam), γ is coefficient reflectivity of electrostatic mirror (the loss of beam
energy through the electrostatic reflector); ξ is the loss (attenuation) in the medium (air) (see
point 8). If no atmosphere, ξ = 0; ς is the loss through beam divergence (ς = 1 if D < Dr
,
where Dr
is diameter of the electrostatic mirror). For a wire net electrostatic reflector 2dw/l
where dw is diameter of wire, l is size of mesh. For example, for the net having a mesh
0.10.1 m, the l = 0.1 m and a wire dw = 0.0001 m, the = 0.002.
Multi-reflex light pressure. The beam pressure, T, of two opposed high reflectors after a
series of reflections, N, to one another is
. 2 ( ) 0
2
( ), ( ) .
2
( )
0 0
2
0
1
0
B S
r
S S
N
j
B j
S T M V V
M V
P
uS
k DV
q V N V
V
P
T V T
(12)
where S is distance between electrostatic reflectors of the station and ship [m], k = 1 1.5 is
correction coefficient for the case when D > Dr
. For primary estimation k = 1.
If VS is small and V is high, the multi-reflex T may be large. For example, if VS =10 m/s,
V = 30 km/s, S is small, the number of reflection may reach n 30000/10/2 = 1500 times
more then regular thrust. That is well for ship trip starting and braking.
88 Alexander Bolonkin
Limitation of reflection number. If the reflector is moved away, the maximum number of
reflections, N, is limited by q > 0, VS < 0.5V (see Eq. (11)). At ship launch or braking the
maximum thrust is limited by a safety acceleration or deceleration.
Coefficient of efficiency. The propulsion efficiency coefficient, η, (without loss for
ionization) may be computed using the equation
TVS PB /
(13)
For full reflection Eq. (13) has the form:
S
S S V V
V
V V V
, 1 for 2
4( )
2 max
(14)
Computation of launch and landing trajectories computed by the usual method of
integration
ai
T/MS
,t
i1
t
it,VS,i1
VS,iait,Si1
SiVS,it
(15)
The results for spaceship having the weight 3 tons and the final speed 12 km/s are
presented in Figure 13 - 15.
Figure 13. Thrust of the multi-reflection beam and the one time reflection beam versus the flight time
and beam flow. Data: = 0.002, = 0, = 1, Dr = 30 m, u = 0.1 m, V = 25000 m/s, Ms = 3000 kg,
acceleration limit Ng < 8g, M0 = M = 1, 2, 3 kg/s.
New Concepts, Ideas and Innovations in Aerospace… 89
Figure 14. Ship speed versus the flight-time and the beam flow. Data: = 0.002, = 0, = 1, Dr =30
m, u = 0.1 m, V = 25000 m/s, Ms = 3000 kg, acceleration limit Ng < 8g, M0= M = 1, 2, 3 kg/s.
Figure 15. Ship speed versus the distance and the beam flow. Data: flight time t = 350 sec., = 0.002,
= 0, = 1, Dr =30 m, u = 0.1 m, V = 25,000 m/s, Ms = 3000 kg, acceleration limit Ng < 8g, M0 = M =
1, 2, 3 kg/s.
90 Alexander Bolonkin
10. For non-relativistic flight all equations are simplify.
C
nV M V
q
m
S ut U
V
u
D
M V
T M V V P
p
S B
2 2
, ,
2
2 ,
2
0
2 2
0
max 0
(16)
where C is an positive electric charge of M0.
Typical computations for Earth and interplanetary space vehicles are presented in Figure
16 - 18 (typical probe, Figure 16 and Moon spaceship, Figures 17, 18, - Project 1).
10. Macro-particle beam and projectile. The developed theory may be applied to any
macro-particle beam or projectiles. An electrostatic gun may be used for its acceleration [27].
The projectile has a charge which is lost after it exits the gun (charged energy will be returned
to installation). There is no big problem with flight through the Earth atmosphere for
projectiles. The loss energy is about 10 - 20%, the heat is small if projectile has a sharp tip
(see [21], [24]). The ship uses a kinetic energy of projectile and projectile matter as described
in [29, 30].
The offered method may be applied variously. We consider only application to
interplanetary spaceship and interstellar space probe.
Figure 16. Maximum thrust (drag) versus the particle beam speed and mass flow [g/s] for typical Earth
satellite.
New Concepts, Ideas and Innovations in Aerospace… 91
Figure 17. Energy is requested for producing of the beam via the beam speed and mass flow for Moon
ship.
Figure 18. Voltage requited for accelerating of beam via a particles speed. The beam is
H2 .
92 Alexander Bolonkin
PROJECT 1
(Interplanetary Spaceship Having Weight 3 tons and Speed 12 km/s,)
Assume we want to estimate the parameters of an interplanetary manned spaceship for
Moon and Mars having weight of 3 tons and a final speed 12 km/s started from Moon, Mars,
or Earth's tower having height of 80 km. We use the theory beam reflection, Figs. 16 - 18 and
find the estimation time, thrust, speed, distance. The trained astronauts can stand the overload
8g.
The request power for beam flow 1, 2, 3 kg/s are 312, 625, 937 MW respectively. Power
for ionization are 127, 254, 391 MW respectively. That is power of a middle electric station.
PROJECT 2
(Interstellar probe having speed 30.000 km/s, weight 100 kg)
Let us assume we want to estimate an interstellar probe which can reach the nearest solar
systems. As known they are located about 3 - 4 light years from our Sun. That means the
apparatus having speed S = 0.1c (VS = 30,000 km/s) can reach them in 30 - 40 years.
Remander, "Voyager-1" was flown for 30+ year, sending information up to present time. But
it has speed only 20 km/s and was reached only the boundary of Solar system (about 2
billions km).
Assume, the weight of interstellar probe is 100 kg. If distance of acceleration is S =
31013 m (200 AU) the acceleration and acceleration time must be
days
a
V
m s t
S
V
a
S S
2 10 sec 23
15
3 10 15 / ,
2 3 10
9 10
2
6
7
2
13
2 14
.
The thrust, requested acceleration energy and power are
GW
t
W
J P
M V
T aM N W S S
S 22.5
2 10
4.5 10 4.5 10 ,
2
100 9 10
2
15 100 1500 ,
6
16
16
2 14
,
The mass of the beam flow, and energy spent by beam station are (Eq. (3),(5))
GW M c
P
k g s
c
T
M
B
S
22.5
2 1 0.01
5 10 9 10 0.01
2 1
5 10 / ,
2 3 10 (0.1 0.05)
1500 1 0.01
2 ( )
1
5 1 6
2
2 2
0
5
8
2
0
Here S = 0 0.1 . We take the average value S = 0.05 . Notice that PB = P, that means
our installation transfer the station energy to ship with efficiency = 1. Unfortunately, this
energy is very high. Tens of electric power stations must accelerate this probe in 23 days. We
New Concepts, Ideas and Innovations in Aerospace… 93
cannot decrease this amount by any methods because that is a minimum energy required by
space probe.
Divergence D for u = 0.01 m/s, voltage U (n =1), and plasma temperature Tp are
4.7 10 .
1
0.01
2
1 9 10
1.6 10
1.67 10
2 1
0.4 10 ,
3 1.38 10
1,67 10 10 10 ,
0.1
3 10
3 10
1 0.01
6
1 6
1 9
2 7
2
2 2
8 0
2 3
1 3 2 2 7 4
8
2
V
nc
q
m
U
K
ik
mu S k m T
c
u
D
p
p
The power of dissociations (H2 H + H, 2.2 eV) and ionization (H H
+
, 13,6 eV) are
equal
kW
m n
M
E e e
p
i d i 75.7
1.67 10 1
5 10 1.6 10 1.6 10 2.2 13.6 27
5
19 0 19
.
In given case (comparison with PB above) this value is small and we can negligee it. But
into planetary flight (V8 - 30 km/s and large M0) this energy is essential.
DISCUSSION
In [34] G.A. Landis writes about using particle beams for interstellar flight. The beam is
braked by a magnetic sail. Unfortunately, as with most other works in this field, his work also
contains only common speculations. No theory, no mathematical models, no computations.
More then ten years authors investigate the magnetic sail, but not its theory, no formulas
which allows correct calculation or to estimate the magnetic sail drug. More over, the most
magseil works contain a common mistake (see Chapter 4 "Electrostatic MagSail"). Landis
offered the beam temperature 45 oK. The theory in this article is shown that this temperature
gives the beam divergence which does not allows the interstellar flights. Absolutely
unsubstantiated statement that magnetic sail reflects beam in thousands kilometers diameter.
The estimations shows for high speed particles especially relativistic particles the affective
diameter equals some meters and magnetic field must be powerful. In additional the magnetic
sail is impossible at present time: electric ring needs in cryogenic temperature and spaceship
must have power cryogenic equipment because the Sun will warm the ring for any heat
insulation; for starting the ring needs a power electric station; a special equipment is
necessary for displacing the ring of 100 km diameter into space; if the ring temperature
exceeds a critical cryogenic temperature in any ring place, the ring explodes. The ring weight
is big (22 tons for diameter 100 km), the produced magnetic field is very weak (10-6
Tesla).
The magnetic sail does not have active control. That means the ship will move in one (noncontrol)
direction and a ship mission will useless. These obvious defects makes impossible
the application of the magnetic sail with little or no progress in solution these problems since
1988.
The suggested method does not require a magnetic sail. That used the electrostatic sail
[26] and AB-Ramjet engine offered by author early. This sail is light (100 - 300 kg), cheap,
94 Alexander Bolonkin
and has tens kilometers (hundreds km for low beam density) of the effective radius. For
example, for solar wind the magnetic effective radius decreases proportional 1/R
2
(where R is
distance of the sail from the Sun), electrostatic effective radius decreases approximately 1/R
(see [26]). That is very important advantage.
CONCLUSION
The offered idea and method use the AB-Ramjet engine suggested by author in 1982 [3,
4, 6, 8, 9, 12, 14 - 16, 18] and detail developed in [28]. The installation contains an
electrostatic particle collector suggested in 1982 and detail developed in [26, 30]. The
propulsion-reflected system is light net from thin wire, which can have a large area (tens km)
and allows to control thrust and thrust direction without turning of net (Figure1). This new
method uses the ultra-cold full neutral relativistic plasma and having small divergence. The
method may be used for acceleration space apparatus (up relativistic speed) for launch and
landing Space apparatus to small planets (asteroids, satellites) without atmosphere. For Earth
offered method will be efficiency if we built the tower (mast) about 40 80 km height [19,
24]. At present time that is the most realistic method for relativistic probe.
REFERENCES
(see some Bolonkin's articles in http://Bolonkin.narod.ru/p65.htm, http://arxiv.org search
"Bolonkin", and book "Non-rocket Space Launch and Flight", Elsevier, London, 2006, 488
ps)
[1] Bolonkin, A.A., (1965a), ―Theory of Flight Vehicles with Control Radial Force‖.
Collection Researches of Flight Dynamics, Mashinostroenie Publisher, Moscow, , pp.
79–118, 1965, (in Russian). Intern.Aerospace Abstract A66-23338# (English).
[2] Bolonkin, A.A., (1982a), Installation for Open Electrostatic Field, Russian patent
application #3467270/21 116676, 9 July, 1982 (in Russian), Russian PTO.
[3] Bolonkin, A.A., (1983a), Space Propulsion Using Solar Wing and Installation for It,
Russian patent application #3635955/23 126453, 19 August, 1983 (in Russian), Russian
PTO.
[4] Bolonkin, A.A., (1983b), Getting of Electric Energy from Space and Installation for It,
Russian patent application #3638699/25 126303, 19 August, 1983 (in Russian), Russian
PTO.
[5] Bolonkin, A.A., (1983c), Protection from Charged Particles in Space and Installation
for It, Russian patent application #3644168 136270, 23 September 1983, (in Russian),
Russian PTO.
[6] Bolonkin, A. A., (1983d), Method of Transformation of Plasma Energy in Electric
Current and Installation for It. Russian patent application #3647344 136681 of 27 July
1983 (in Russian), Russian PTO.
[7] Bolonkin A.A., (1983e) Method for Transfer of Plasma Energy in Electric Current and
Installation for it. Russian patent application #3601164/25 086973 of 6 June, 1983 (in
Russian), Russian PTO.
New Concepts, Ideas and Innovations in Aerospace… 95
[8] Bolonkin, A. A.,(1983f), Transformation of Energy of Rarefaction Plasma in Electric
Current and Installation for it. Russian patent application #3663911/25 159775, 23
November 1983 (in Russian), Russian PTO.
[9] Bolonkin, A. A., (1983g), Method of a Keeping of a Neutral Plasma and Installation for
it. Russian patent application #3600272/25 086993, 6 June 1983 (in Russian), Russian
PTO.
[10] Bolonkin, A.A., (1983i), Method of Energy Transformation of Radioisotope Matter in
Electricity and Installation for it. Russian patent application #3647343/25 136692, 27
July 1983 (in Russian), Russian PTO.
[11] Bolonkin, A.A., (1983j), Method of stretching of thin film. Russian patent application
#3646689/10 138085, 28 September 1983 (in Russian), Russian PTO.
[12] Bolonkin, A.A., (1987), ―New Way of Thrust and Generation of Electrical Energy in
Space‖. Report ESTI, 1987, (Soviet Classified Projects).
[13] Bolonkin, A.A., (1990), ―Aviation, Motor and Space Designs‖, Collection Emerging
Technology in the Soviet Union, 1990, Delphic Ass., Inc., pp.32–80 (English).
[14] Bolonkin, A.A., (1991), The Development of Soviet Rocket Engines, 1991, Delphic
Ass.Inc.,122 p. Washington, (in English).
[15] Bolonkin, A.A., (1992a), ―A Space Motor Using Solar Wind Energy (Magnetic Particle
Sail)‖. The World Space Congress, Washington, DC, USA, 28 Aug. – 5 Sept., 1992,
IAF-0615.
[16] Bolonkin, A.A., (1992b), ―Space Electric Generator, run by Solar Wing‖. The World
Space Congress, Washington, DC, USA, 28 Aug. –5 Sept. 1992, IAF-92-0604.
[17] Bolonkin, A.A., (1992c), ―Simple Space Nuclear Reactor Motors and Electric
Generators Running on Radioactive Substances‖, The World Space Congress,
Washington, DC, USA, 28 Aug. – 5 Sept., 1992, IAF-92-0573.
[18] Bolonkin, A.A. (1994), ―The Simplest Space Electric Generator and Motor with
Control Energy and Thrust‖, 45th International Astronautical Congress, Jerusalem,
Israel, 9–14 Oct., 1994, IAF-94-R.1.368 .
[19] Bolonkin A.A., (2003), Optimal Inflatable Space Towers with 3 - 100 km Height, JBIS,
Vol.56, No.3/4. 2003, pp. 87 - 97.
[20] Bolonkin A.A., (2003), Hypersonic Space Launcher, Actual Problems of Aviation and
Space Systems, Kazan, 8 (15), pp.45 - 68.
[21] Bolonkin A.A., (2003), Asteroids as Propulsion System of Space Ships, JBIS, Vol.56,
No.3/4, pp. 98 -107.
[22] Bolonkin A.A., (2003), Non-Rocket Transport System for Space Travel, JBIS, Vol.56,
No. 7/8, pp. 231 - 249.
[23] Bolonkin A.A., (2004), Hypersonic Gas-Rocket Launcher of High Capacity, JBIS,
Vol.57, No.5/6, pp.162 - 172.
[24] Bolonkin A.A., (2004), Kinetic Space Towers and Launchers, JBIS, Vol.57, No.1/2.
2004, pp. 33 - 39.
[25] Bolonkin A.A., (2004), Multi-Reflex Propulsion Systems for Space and Air Vehicle
and Energy Transfer for Long Distance, JBIS, Vol.57, No.11/12. 2004, pp. 379 - 390.
[26] Bolonkin A.A., (2005), Electrostatic Solar Wind Propulsion System, AIAA-2005-3653.
41-st Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
96 Alexander Bolonkin
[27] Bolonkin A.A. (2006), Electrostatic AB-Ramjet Space Propulsion, AIAA-2006-6173,
AIAA/AAS Astrodynamics Specialist Conference, 21-24 August 2006, USA. AEAT,
Vol. 79, No. 1, 2007, pp. 3-16.
[28] Bolonkin A.A., (2006), Optimal Space Tower (Mast), Presented as paper AIAA-2007-
0367 to 45th AIAA Aerospace Science Meeting, 8 - 11 January 2007, Reno, Nevada,
USA. (See details in author's works: AIAA-2006-4235, AIAA-2006-7717).
http://arxiv.org.
[29] Bolonkin A.A., (2006), Linear Electrostatic Engine, Presented as AIAA-2006-5229 for
42 Joint Propulsion Conference, Sacramento, USA, 9-12 July, 2006. http://arxiv.org.
[30] Bolonkin A.A., (2006), Non-Rocket Space Launch and Flight, Elsevier, London, pp.
488. Contents is in http://Bolonkin.narod.ru/p65.htm.
[31] Kikoin I.K., (1976), Table of Physical Magnitudes, Moscow, Atomic Publish House.
[32] Fedorov V.D., (1981), Basis of Rocket Flight, Moscow, Nauka.
[33] Landis G.A., (2004), Interstellar Flight by Particle Beam, Acta Astronautica, Vol. 55,
pp.931 - 934.
New Concepts, Ideas and Innovations in Aerospace…
Attachment to Part A, Ch.3. Possible form of Space Ships and Space Stations
98 Alexander Bolonkin
New Concepts, Ideas and Innovations in Aerospace… 99
Chapter 4
THEORY OF SPACE MAGNETIC SAIL .
SOME COMMON MISTAKES
AND ELECTROSTATIC MAGSAIL
ABSTRACT
The first reports on the ―Space Magnetic Sail‖ concept appeared more 30 years ago.
During the period since some hundreds of research and scientific works have been
published, including hundreds of research report by professors at major famous
universities. The author herein shows that all these works related to Space Magnetic Sail
concept are technically incorrect because their authors did not take into consideration that
solar wind impinging a MagSail magnetic field creates a particle magnetic field opposed
to the MagSail field. In the incorrect works, the particle magnetic field is hundreds times
stronger than a MagSail magnetic field. That means all the laborious and costly
computations in revealed in such technology discussions are useless: the impractical
findings on sail thrust (drag), time of flight within the Solar System and speed of
interstellar trips are essentially worthless working data! The author reveals the correct
equations for any estimated performance of a Magnetic Sail as well as a new type of
Magnetic Sail (without a matter ring).
Keywords: magnetic sail, theory of MagSail, space magnetic sail, Electrostatic MagSail.
INTRODUCTION
The idea of utilizing the magnetic field to aggregate matter in space, harnessing a drag
from solar wind or receiving a thrust from an Earth- charged particle beam is old. The
MagSail is a gigantic (more than 50 -100 km in radius) super-conductive ring located in outer
space that produces a magnetic field and reflects the impinging solar wind, or a particle
beamed from the Earth. Unfortunately, the currently used theory for computation of drag
from solar wind or thrust from particle beam is complex. The magnetic field changes in
Presented as Bolonkin’s paper AIAA-2006-8148 to 14th AIAA/AHI Space Planes and Hypersonic Systems and
Technologies Conference, 6 - 9 Nov 2006 National Convention Centre, Canberra, Australia.
100 Alexander Bolonkin
widely diapason, every particle moves in its own trajectory and it is exquisitely difficult to
accurately estimate a summary drag. Over the years, many space researchers have offered
many equations for drag estimation that give remarkably different results. However, no
known equations take into proper consideration the magnetic field of particles moved in a
ring-shaped magnetic field. These particles create their own magnetic field that is OPPOSED
to the MagSail‘s magnetic field. This magnetic field of charged particles can be stronger—by
hundreds times—than a ring field. It can fully deactivate the MagSail magnetic field.
The simplest computation shows a profound mistake in all known works. Some of them
presented in [1]-[39].
Take the typical MagSail ring: radius of ring is R = 50 km, electric current I =104 A. The
intensity H1 of magnetic field in center of ring is
0.1 A/m
2 5 10
10
2
4
4
1
R
I
H , (1)
This intensity is approximately same of the ring as well as near it. We assume in our
subsequent computation that H1 = constant.
Take the typical solar wind flows into ring at distance from Sun 1 AU (the Earth‘s orbit
about its primary star) with average wind speed V = 400 km/s, and density N = 107
1/m3
. The
solar wind contains electrons and protons. Within the ring magnetic field they rotate under
Lawrence force and produce their own magnetic field that is OPPOSED to the ring magnetic
field, decreases it (diamagnetic property), and pumps the ring magnetic energy into energy of
its own magnetic field (summary energy is constant). This magnetic field from the rotated
electrons (we here neglect the additional magnetic field from the rotated protons) can be
estimated by equations (we consider only electrons into the ring):
1 0 1
2
1
2
, ,
/
,
2
i R qNV B H
q m B
V
r
r
i
H
e
(2)
where H2 is magnetic intensity from rotated solar wind electrons, A/m; r is electron gyroradius,
m; i is electric currency of solar wind electrons, A; V = 400 km/s is average solar wind
speed, B1 is magnetic intensity, T; 0 = 410-7
is magnetic constant.
Substituting our values, we received r = 18.2 m; i = 5024 A; H2 = 276 A/m. The last
magnitude shows that the magnetic intensity of solar wind electrons is in 2760 times greater
(H2 >> H1) than the ring magnetic intensity of MagSail! It is correct for any charged beam
that interacts with the MagSail. That means all research and computation (without an
influence the solar wind or charged beam into MagSail) is wrong and basically worthless for
all practical space exploration and exploitation applications.
How can it happen that hundreds of researchers, professors at famous universities,
audiences of specialists, members of scientific Conferences and Congresses, editors of
scientific journals: "Journal of Propulsion and Power", (Editor V. Yang); Journal "Spacecraft
and Rockets", (Editor V. Zoby), paid so little attention to student-level mistakes in many
scientific publications and public presentations to scientific conferences? More over, the
director NASA Institute for Advanced Concepts (NIAC) Mr. R. Cassanova awarded (totaling
New Concepts, Ideas and Innovations in Aerospace… 101
more than $1 million dollars!) to his close associate, professor R.M. Winglee (University of
Washington) for pseudo-scientific work about MagSail [1] #
.
It is still happening because popular textbook authors continue to consider the interaction
between the strong magnetic field of particle accelerators and small amount of charged
particles where we can neglect the influence of charged particles in magnetic field of the
accelerator. With MagSail‘s, we have the opposed situation: the weak ring magnetic field and
strong magnetic field of solar sail or charged beam.
THEORY
Below, the author suggests the correct theory of MagSail operation, which takes into
consideration the influence of the solar wind flow into the ring magnetic field and allows an
estimation of the drag of MagSail.
Let us to take the equations (2) in form:
, , ( )
/
,
/
,
2
, 0 1 2
2
2 2 3
1
1
i R qNV B H H
q m B
V
R
q m B
V
r
r
i H
R
I H
e p
(3)
where mp is mass of positive particle, for proton mp = 1.6710-27, kg; R2 is rotate radius of
positive particles (protons for Solar Wind), m; R3 is capture radius of positive particles, m.
Notice particularly the last equation (3). In this equation, the active is summary magnetic
intensity B!
For getting the maximum solar wind drag the turn radius of heavy particles must be 90
degrees. Assume R=R1=R2=R3. We have 6 equations (3) and 6 unknown values. From set
equations (3) we receive the estimation of the radius efficiency R:
0
2
2 2
m V
I q
q N
m
R
p
e
(4)
From (4) we get minimal ring electric currency
q
m V
I
p
0
2
(5)
For average solar wind speed V = 400 km/s the minimal ring electric currency is I =
6.65103 A.
# Mr. Cassanova invented a new method of legal larceny of government money. He personally awarded taxpayerfunded
money grants to his friends, protégés and other useful persons for mere promises of great discoveries
and revolutionary developments in future in space sciences. In nine years of NIAC‘s existence under him, Mr.
Cassanova spent in excess of fifty millions dollars of taxpayer money in pseudo-scientific works, but has not
presented to the public even one new researched scientific concept. The Scientific Committee of a famous
organization, the CAGW (Citizen Against Government Waste), awarded NIAC and Mr. Cassanova pseudoNobel
prize-2005 and 2006 [42]-[45].
102 Alexander Bolonkin
The solar wing drag, D, equals approximately
2 2 D R mpNV
(6)
Results of computation are presented in figures 1 - 2. Look you attention: for receiving
good drag we need in high electric current. For typical current I = 104 A (I = 10 kA) the
efficiency radius R and drag D are small.
Figure 1. Radius efficiency of MagSail via ring electric current.
New Concepts, Ideas and Innovations in Aerospace… 103
Figure 2. Drag of MagSail via ring electric current at distance from Sun equals 1 Astronomical Unit.
NEW ELECTROSTATIC MAGSAIL (EMS)
The conventional MagSail with super-conductive ring has big drawbacks:
1. It is very difficult to locate gigantic (tens of km radius) ring in outer space.
2. It is difficult to insert a big energy into superconductive ring.
3. Super-conductive ring needs a low temperature to function at all. The Sun heats all
bodies in the Solar System to a temperature higher then temperature of superconductive
materials.
4. The super-conductive ring explodes if temperature is decreased over critical value.
5. It is difficult to control the value of MagSail thrust and the thrust direction.
The author offers new Electrostatic MagSail (EMS). The innovation includes the central
positive charged small ball and a negative electronic equal density ring rotated around the ball
(Figure 3).
Figure 3. Electrostatic MagSail. Notations: 1-Spaceship; 2-Positive charged ball; 3–electrical ring; 4-
solar wind; 5-EMS drag. In right side the EMS in turn position.
The suggested EMS has the following significant advantages in comparison with
conventional MagSail:
(1) No heavy super-conductive large ring.
(2) No cooling system for ring is required.
(3) Electronic ring is safe.
(4) The thrust (ring radius) easy changes by changing of ball charge.
ELECTROSTATIC MAGSAIL THEORY
Let us consider a method of estimation of electronic ring magnetic intensity in the
electronic ring‘s center [2]. We will take into consideration a repulsion of electrons from
electron ring (blocking the ball charge by the electronic ring) and relativistic speed of
104 Alexander Bolonkin
electrons. We will not take into consideration diamagnetic property of solar wind or charged
beam because our purpose here is only to find the magnetic intensity from electronic ring.
The blocking the MagSail magnetic field by the particles flow the reader find in previous
section (above). We also neglect the radiation of rotary electronic ring because the ring is
right circle, has constant density and that does not emit synchronous radiation (this
assumption needs further research. Synchronous radiation appears when electrons rotate in
outer magnetic field, the electron ring is unclosed or has non-constant density. In our case the
ring electric and magnetic fields are constant and not emit energy in outer space).
From equilibrium of the centrifugal and attraction forces we have
, , ,
( )
1 2
2
2
1 2 2
2
Q Q
q
Q M m
R
Q Q Q
k
R
MV
e
e
(7)
where M is mass of electron ring, kg; Ve
is speed of electrons, m/s; R is ring radius, m; k =
9109
is electrostatic constant; Q1 is positive charge of the central ball, C; Q2 is negative
charge of the electron ring, C; me
is mass of electron, kg; q = 1.610-19 is electron charge, C.
The best relation between Q1 and Q2 is Q1 = 2Q2. Substitute this value into (7) we receive
B H
R
Q V
I
R
I
H
k q m
RV Q
R
Q
m
q
V k
e
e
e
e
e 0
2
2
2
2 2
,
2
,
2
,
/
,
(8)
where I is ring electric currency, A; H is magnetic intensity, A/m; B is magnetic intensity, T;
0 = 410-7
is magnetic constant.
Substitute the previous Eqs. (8) in the last equation (8) for B and use the formula for
relativistic electron mass
,
4 1
/
,
1
, ,
4 /
2
3
0
3
0
2
0
3
0
Rk
c m q
B
m
m
c
V
k q m
V
R
B
e e
e
e
e
e
(9)
where c = 3108 m/s is light speed; me0 = 9.1110-31 kg is electron mass at Ve = 0.
Let us to add formula for estimation charge and radius of ball and substitute the known
values into last equation (9). We received the final equations for estimation of MagSail size:
0
2 2
2
2
0
2
2
2
3
3
0
2
3
3 2
,
/ 1
,
1
1
, 1.36 10
1
1
1.7 10
E
k Q
a
k q m
c R Q
R
B H
R
B
e
(10)
where a is radius of ball, m; E0 is safety electric intensity at ball surface, V/m.
If the magnetic intensity into ring is constant, we can estimate the energy needed for
starting of ring:
New Concepts, Ideas and Innovations in Aerospace… 105
2
,
2 2
,
2
, Φ
2
2
0 0 0
L I W
R
R
S
S I L L
R
I
R
I
H
(11)
where is magnetic flux, Wb: L is ring inductance, Henry; S is ring area, m2
; final equation
in (11) W is energy, J. For conventional ring of MagSail having R = 50 km and I = 104 A the
W = 5106
J.
The Eqs. (7) - (11) allow to find magnetic intensity of MagSail for given ring radius and
electron speed (without solar wind or plasma beam), charge and radius of ball for given
electrostatic ball intensity, energy of rotate ring, but they do not permit to estimate a MagSail
drag. We can estimate drag of conventional MagSail (see section above), to compute the drag
of electrostatic sail offered by author in [3] Chapter 18, but unfortunately we cannot to
estimate for the drag EMS in the time present. The trajectory of charged particle into both
field (magnetic and electric) are very complex.
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: Bolonkin, and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[39] (Respectively). Some Manuscripts about MagSail published or presented to AIAA
Conferences: (1) Winglee R.,M., at al. (4 co-authors), "Mini-Magnetospheric Plasma
Propulsion. Tapping the Energy of the Solar Wing for Spacecraft Propulsion", Journal
of Geophysical Reserach. Vol. 105, No. 6., 2000. (2) AIAA-2006-5257, (3) AIAA2006-769
(4 coauthors). (4) JSP 2006, Vol. 43, no. 3, (667-672). (5) AIC-05-C4.6.07.
(6) AIAA-2005-4463 (6 coauthors). (7) AIAA-2005-4791. (8) AIAA-2005-4461. (9)
AIAA-2004-3502 (7 co-authors). (10) AIAA-2003-4292 (8 co-authors). (11) IAC-03-
5.6.06. (12) AIAA-2003-4886. (13) AIAA-2003-4292. (14) AIAA-2003-6201. (15)
AIAA-2003-5226. (16) AIAA-2003-5227. (17) "Journal Propulsion and Power (JPP)"
2003, Vol.19, no 6 (1129-1134). (18) JPP, vol.20, No 4 (763-764). (19) JPP, vol.21,
No. 5, 2005 (853-861)(4 co-authors). (20) AIAA-2004-3706. (21) AIAA-2001-840.
(22) AIAA-2001-3517. (23) AIAA-1998-3403. (24) AIAA-1997-3072. (25) AIAA1997-3208.
(26) AIAA-1997-2792 (3 co-authors). (27) Journal "Spacecraft and
Rockets". 1994, Vol. 31, No. 2 (342 - 344). (28) AiAA-1992-3862. (29) AIAA-1991-
2538. (30) AIAA-1991-3352. (31) AIAA-1990-2367. (32) AIAA-1990-1997 (6 coauthors).
(33) AIAA-1990-3799. (34) AIAA-1989-2861, (35) JSR 1991, Vol. 28, no.2,
(197-203). (36) AIAA-1990-1997. (37) AIAA-1990-2367. (39) AIAA-1990-3799. (39)
AIAA-1989-2941.
[40] Bolonkin A.A., "A Space Motor Using Solar Wind Energy (Magnetic Particle Sail)",
IAF-0615. The World Space Congress, 28 August - 5 September 1992, Washington
DC, USA.
[41] Bolonkin A.A., Non-Rocket Space Launch and Flight, Elsevier, London, 2006, 488 pgs.
[42] GO TO: http://auditing-science.narod.ru or http://www.geocities.com/auditing.science/
[43] GO TO: http://NASA-NIAC.narod.ru.
[44] Johnson A., Space Research: Organizing for Economical Efficiency. Presented as paper
AIAA-2006-7224 in Conference "Space-2006", 19-21 September 2006, San Diego,
California, USA.
106 Alexander Bolonkin
[45] Johnson A., Space research: problems of efficiency. Journal "Actual Problems of
Aviation and Aerospace System", No.1, 2007.
http://www.kcn.ru/tat_en/science/ans/journals/rasj_cnt/07_1_10.html
Attachment to Part A, Ch. 4. Possible forms of Space Ships
New Concepts, Ideas and Innovations in Aerospace… 107
New Concepts, Ideas and Innovations in Aerospace…
New Concepts, Ideas and Innovations in Aerospace…
Chapter 5
HIGH SPEED AB-SOLAR SAIL
ABSTRACT
The Solar sail is a large thin film used to collect solar light pressure for moving of
space apparatus. Unfortunately, the solar radiation pressure is very small about 9 N/m2
at Earth's orbit. However, the light force significantly increases up to 0.2 - 0.35 N/m2
near
the Sun. The author offers his research on a new revolutionary highly reflective solar sail
which flyby (after special maneuver) near Sun and attains velocity up to 400 km/sec and
reaching far planets of the Solar system in short time or enable flights out of Solar
system. New, highly reflective sail-mirror allows avoiding the strong heating of the solar
sail. It may be useful for probes close to the Sun and Mercury and Venus.
Keywords: AB-solar sail, highly reflective solar sail, high speed propulsion.
1.INTRODUCTION
A solar sail is a thin film reflector that uses solar energy for propulsion. The spacecraft
deploys a large, lightweight sail which reflects light from the Sun (or some other source). The
radiation pressure on the sail provides thrust by reflecting photons. The solar radiation
pressure is very small 6.7 Newtons per gigawatt. That equals 9.1210-6 N/m2
at Earth's orbit
(1 AU - Astronomic Unit = 150 million km) and decreases by the square of the distance from
the sun. However, the solar light pressure significently increases near sun and not far above it
can reach 0.2 - 0.35 (up o.4 on Solar surfice) N/m2
.
Brief history. The conventional solar sail concept was first proposed by Friedrich Zander
in 1924 [1] and gradually refined over the decades. The author proposed innovations and a
new design of Solar sail in 1965 [2, 3], and theory was developed in [3] -[6]. Author offers a
new revolutionary solar AB-sail. Main particularity this sail is very high reflectivity which
allows the AB-sail to come very close to the Sun without great heating and to attain high light
force and high speed.
This work is presented as Bolonkin‘s paper AIAA-2006-4806 for 42 Joint Propulsion Conference, Sacramento,
USA, 9-12 July, 2006.
112 Alexander Bolonkin
This innovation allows (main advantages only): 1) to achieve very high speed up 400
km/s; 2) easy to control an amount and direction of thrust without turning a gigantic sail; 3) to
utilize the solar sail as a power generator (for example, electricity generator); 4) to use the
solar sail for long-distance communication systems.
Short information about Sun. The pressure of light equals P = 2E/c (where E is energy of
radiation, c is light speed (c = 3108 m/s)). The solar light energy at Earth's orbit equals 1.4
kW/m2
, but near a solar surface it reaches up to 64103
kW/m2
(it increases 47 thousand
time!). As the result the light pressure jumps up to 0.4 N/m2
. The space apparatus can get
significant acceleration (up to 80 m/s2
) and high speed up to 400 - 500 km/s.
Spectrum of Sun is presented in Figure 1. Note, the space mirror (sail) will not heat only
if it reflects all solar spectrum ( = 0.2 3 m, 200 ÷ 3000 nm).
Figure 1. Spectrum of solar radiation. is the wavelength [0.2–2.7 μm, 200 ÷ 2700 nm].
2. DESCRIPTION AND INNOVATIONS
Description. The suggested AB space sail is presented in Figure 2. It consists of: a thin
high reflection film (solar sail) supported by an inflatable ring (or other method), space
apparatus connected to solar sail, a heat screen defends the apparatus from solar radiation.
The thin film includes millions of very small prisms (angle 45o
, side 3 30 m). The
solar light is totally reflected back into the incident medium. This effect is called total internal
reflection. Total internal reflection is used in the proposed reflector. As it is shown in [5]
Ch.12 the light absorption is very small (10-5
10-7
) and radiation heating is small (see
computation section).
Another possible design for the suggested solar sail is presented in Figure 3. Here solar
sail has concave form (or that plate is made like Fresnel mirror).
New Concepts, Ideas and Innovations in Aerospace… 113
Figure 2. High reflective space AB-sail. (a) Side view of AB-sail; (b) Front view; (c) cross-section of
sail surface; (d) case of non-perpendicular solar beam; (e) triangle reflective sell. Notation: 1 - thin film
high reflective AB-mirror, 2 - space apparatus, 3 - high reflective heat screen (shield) of space
apparatus, 4- inflatable support thin film ring, 5 - inflatable strain ring, 6 - solar light, 9 - solar beam, 10
- reflective sell, 11 - substrate, 12 - gap.
Figure 3. AB highly reflective solar sail with concentrator. (a) side view; (b) front view. Notation: 1 -
highly reflective AB mirror (it may have a Fresnel form), 2 - space apparatus, 3 - high reflective heat
screen, 4 - control mirror, 5 - reflected solar beam, 6 - inflatable support thin film ring, 7 - inflatable
strain ring, 8 - thin transparent film, 9 - solar beam.
The sail concentrates solar light on a small control mirror 4. That mirror allows redirected
(reflected) solar beam and to change value and direction of the sail thrust without
turning the large solar sail. Between thin films 1, 8 there is a small gas pressure which
supports the concave form of reflector 1. Concentration of energy can reach 103
104
times,
temperature greater than 5000 oK. This energy may be very large. For the sail of 200200 m,
114 Alexander Bolonkin
at Earth orbit the energy is 5.6104
kW. This energy may be used for apparatus propulsion or
other possibilities (see [5]), for example, to generate electricity. The concave reflector may be
also utilized for long-distance radio communication.
The trajectory of the high speed solar AB-sail is shown in Figure 4. The sail starts from
Earth orbit. Then is accelerated by a solar light to up 11 km/s in opposed direction of Earth
moving around Sun and leaves Earth gravitational field. The Earth has a speed about 29 km/s
in its around Sun orbit. The sail will be have 29 -11=18 km/s. That is braked and moves to
Sun (trajectory 4). Near the Sun the reflector is turned for acceleration to get a high speed (up
to 400 km/s) from a powerful solar radiation. The second solar space speed is about 619 km/s.
If AB sail makes three small revolutions around Sun, it can then reach speed of a 1000 km/s
and leaves the Solar system with a speed about 400 km/s. Suggested highly reflective screen
protects the apparatus from an excessive solar heating. Note, the offered AB sail allows also
to brake an apparatus very efficiency from high speed to low speed. If we send AB sail to
another star, it can brake at that star and became a satellite of the star (or a planet of that solar
system).
Figure 4. Maneuvers of AB solar sail for reaching a high speed: braking for flyby near Sun, great
acceleration from strong solar radiation and flight away to far planets or out of our Solar system.
Notation: 1 - Sun, 2 - Earth, 3 AB Solar sail, 4 - trajectory of solar sail to Sun, 5 - other planets, 6, 7 -
speed of solar sail.
3. ESTIMATION AND COMPUTATION
1. Light Pressure is Calculated by Equation
c
E
p
c
E
p (1 ) , for 1,
2
(1)
where p is light pressure, N/m2
; E is energy, J/m2
; c = 3108 m/s is light speed; is reflective
coefficient ( = 0 1). At solar surface E = 64 103 kW/m2
and p = 0.4 N/m2
. At Earth's
orbit the E = 1.4 kW/m2
and p = 9 N/m2
.
2. Temperature of Sail equals
4
1 2
( )
100
S
c
E
T
(2)
New Concepts, Ideas and Innovations in Aerospace… 115
where T is temperature, oK; E is heat flow, W/m2
; is absorption coefficient of light energy,
cS = 5.67 is coefficient, 0 < <1 is coefficients of blackness (emissivity) of two sail sides.
In [5] Ch. 12, Annt. #3 it is shown the absorption coefficient may reaches = 10-7
for
suggested mirror. If it is taken =10-4
, 1 = 2 = 0.9, the sail temperature near the Sun will be
about 500 oK. That temperature is safe for many dielectric materials. The tangential sail speed
in nearest point to Sun reaches 600 km/s and time of AB sail abiding near Sun is only some
minutes.
3. Mass of offered solar sail. a) Estimation of prism mass. Let us take the prisms
having the height = 3 m. That is enough for full reflection 0.9999 of solar
spectra radiation (fig.1). The specific density dielectric material of prism is d1 =
0.8 3.5 g/cm3
. The average mass of S = 1 m2
reflective prism is
3 6 3 2 2
1 mp
1/3 d S (1/3)1.810 310 11.810 k g/ m 1.8 g / m
, (3)
b) Estimation of support film mass. Let us take the support film = 1 m, the
specific density of support material is d2 = 1.8 g/cm3
. The average mass of S = 1
m
2
substrate film is
3 6 3 2 2
2 mf d S 1.810 110 11.810 k g/ m 1.8 g / m
(4).
The total mass of 1 m2
offered sail is
2
m mp mf 1.81.8 3.6 g / m . (5)
Together with mass of an inflatable ring and filaments connected the sail to
apparatus we take the 1 m2
sail mass m = 5 g/m2
. Then the total mass of S =
200200 m offered sail is
MS mS 0.005 4 10 200 k g 4
. (6)
If apparatus mass is Ma = 100 kg, the total ship mass is M = MS + Ma = 300 kg.
There are enough of dielectric material (for example, carbonate) which do not change
their properties up temperature 600 - 800 C.
4. Trajectory and Speed
The apparatus (sail) radial speed and flight time can be estimated by equations [5] p.322.
max
max 0
0
2
0
2
, 2 , , ,
1 1
2
V
s M A d t
M M
pA V as a
s s
V as S
S a
(7)
116 Alexander Bolonkin
where: V is radial sail speed, m/s; Vmax is maximum radial sail speed, m/s; a is initial
(maximal) sail acceleration, m/s2
; s is distance of the sail from a Sun center, m; s0 is minimal
distance, m; p = (0.25 0.4) is maximal light pressure [Eq.(1)], N/m2
; MS is mass of sail; A is
sail area, m
2
; d = (0.001 0.005) is specific mass of sail, kg/m2
; t is flight time from Sun to
far planets, sec.
For example: If A = 200200 = 4104
m
2
, d = 0.005 kg/m2
, p = 0.3 N/m2
, Ma= 100 kg,
that a = 40 m/s2
. The period of an elliptic rotation of apparatus around Sun or planet may be
computed by equation
2
0 0
3/ 2
1 1
,
2
a K g s
K
T
(8)
where T1 is period of rotation, sec; a1 is semi-axis of big axis of ellipse, m; g0 is planet (star)
gravitation at distance s0, m/s2
, (for Sun K 1.331020
m
3
/s2
; g0 274 m/s2
; s0 700106
m;
for Earth K 41014
m
3
/s2
, g0 9.81 m/s2
; s0 5.378106 m).
Computations are presented in Figure 5 - 7. It can be seen that the AB sail can reach very
high speed (up 400 km/s) at distance 10 millions km (< 1 AU) from Sun and a purview of
Solar System . The flight time from Sun to the far planets is short time if we use the AB space
sail (to Pluto about 150 days). But we must add a time of braking (from 29 km/s to 1 km/s)
and about 65 days moving from Earth orbit to Sun (trajectory 4 in Figure 4).
The main particularity of offered AB-sail-reflector is special layer with very high
reflectivity in the full main range of a solar spectrum (Figure1) from 0.1 to 5 m. That means
the temperature of offered sail will be significantly lower then the solar temperature and safe,
allowable operating for offered layers and AB-sail-reflector.
Figure 5. Approximately radial AB-sail speed versus distance from Sun for several initial accelerations
a (acceleration at minimum distance from Sun).
New Concepts, Ideas and Innovations in Aerospace… 117
Figure 6. Maximal sail speed versus initial sail acceleration.
Figure 7. Trip time from Sun to far planets versus a distance from Sun.
The other particularity is special selective coating which has high thermal emissions close
to absolute black body in widely range of solar spectrum.
118 Alexander Bolonkin
Figure 8. Possible Solar Sail.
DISCUSSION
The conventional mirror or multilayer dielectric mirror [12] is useless in this case. They
have a high reflectivity only in narrow range of solar spectrum (Figure 1) and decrease the
adsorbed solar energy up 2 - 5%. The solar surface has temperature about 5800 oK and melts
any dielectric layers together with sail-mirror.
CONCLUSION
The suggested new AB sail can fly very close to the Sun's surface and get high speed
which is enough for quick flight to far planets and out of our Solar System. Advantages
allow: 1) to get very high speed up 400 km/s; 2) easy to control an amount and direction of
thrust without turning a gigantic sail; 3) to utilize of the solar sail as a power generator (for
example, electricity generator); 4) to use the solar sail for long-distance communication
systems.
The same researches were made by author for solar wind sail and other propulsion [7]-
[11].
REFERENCES
(Reader can find part of these articles in author WEB page:
http://Bolonkin.narod.ru/p65.htm, http://arxiv.org, and in the book "Non-Rocket Space
Launch and Flight", Elsevier, London, 2006,488 pgs.)
[1] Tsander, K., From a Scientific Heritage, NASATFF-541, 1967 (quoting 1924 report).
[2] A.A. Bolonkin, ―Theory of Flight Vehicles with Control Radial Force‖. Collection
Researches of Flight Dynamics, Mashinostroenie, Moscow, 1965, pp. 79–118 (in
Russian).
New Concepts, Ideas and Innovations in Aerospace… 119
[3] A.A.Bolonkin, ―Solar Sail Engine for Spaceships‖. Patent (Author certificate #
1262870), priority since 10 January 1985, USSR Patent Office.
[4] A.A. Bolonkin, ―Guided Solar Sail and Electric Generator‖, AIAA-2005-3857, 41st
Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[5] A.A. Bolonkin, Non-Rocket Space Launch and Flight, Elsavier, London, 2006, 488 ps.
[6] A.A. Bolonkin, ―Method of stretching of thin film‖. Russian patent application
#3646689/10 138085, 28 September 1983 (in Russian), Russian PTO.
[7] A.A.Bolonkin, Electrostatic AB-Ramjet Space Propulsion, AIAA-2006-6173.
http://arxiv.org.
[8] A.A. Bolonkin A.A., Beam Space Propulsion, AIAA-2006-7492. http://arxiv.org.
[9] A.A. Bolonkin A.A., Electrostatic Linear Engine, AIAA-2006-4806. AEAT, Vol.78,
No. 6, 2006, pp. 502-508.
[10] A.A. Bolonkin A.A., Suspended Air Surveillance System, AIAA-2006-6511.
http://arxiv.org.
[11] A.A. Bolonkin A.A., Optimal Solid Space Tower (Mast), http://arxiv.org.
[12] G. Landis, "Dielectric Films for Solar- and Laser-pushed Lightsails," AIP Conference
Proceedings Volume 504, pp. 989-992; Space Technology and Applications
International Forum (STAIF-2000), Jan. 30 - Feb. 3, Albuquerque NM.
120 Alexander Bolonkin
Attachment to Part A, Ch. 5. Possible form of Solar Sails
New Concepts, Ideas and Innovations in Aerospace… 121
122 Alexander Bolonkin
New Concepts, Ideas and Innovations in Aerospace…
Chapter 6
TRANSFER OF ELECTRICITY IN OUTER SPACE
ABSTRACT
Author offers conclusions from his research of a revolutionary new idea -
transferring electric energy in the hard vacuum of outer space wirelessly, using a plasma
power cord as an electric cable (wire). He shows that a certain minimal electric currency
creates a compressed force that supports the plasma cable in the compacted form. A large
energy can be transferred hundreds of millions of kilometers by this method. The
required mass of the plasma cable is only hundreds of grams. He computed the
macroprojects: transference of hundreds kilowatts of energy to Earth's Space Station,
transferring energy to the Moon or back, transferring energy to a spaceship at distance
100 million of kilometers, the transfer energy to Mars when one is located at opposed
side of the distant Sun, transfer colossal energy from one of Earth's continents to another
continent (for example, between Europe-USA) wirelessly—using Earth's ionosphere as
cable, using Earth as gigantic storage of electric energy, using the plasma ring as huge
MagSail for moving of spaceships. He also demonstrates that electric currency in a
plasma cord can accelerate or brake spacecraft and space apparatus.
Keywords: transferring of electricity in space; transfer of electricity to spaceship, Moon,
Mars; plasma MagSail; electricity storage; ionosphere transfer of electricity.
INTRODUCTION
The production, storage, and transference of large amounts of electric energy is an
enormous problem for humanity, especially of energy transfer in outer space (vacuum). These
spheres of industry are search for, and badly need revolutionary ideas. If in production of
energy, space launch and flight we have new ideas (see [1]-[16]), it is not revolutionary ideas
in transferring and storage energy except the work [4].
However, if we solve the problem of transferring energy in outer space, then we solve the
many problems of manned and unmanned space flight. For example, spaceships can move
Presented as Bolonkin‘s paper AIAA-2007-0590 to 45th AIAA Aerospace Science Meeting, 8 - 11 January 2007,
Reno, Nevada, USA.
124 Alexander Bolonkin
long distances by using efficient electric engines, orbiting satellites can operate unlimited
time periods without entry to Earth's atmosphere, communication satellites can transfer a
strong signal directly to customers, the International Space Station‘s users can conduct many
practical experiments and the global space industry can produce new materials. In the future,
Moon and Mars outposts can better exploration the celestial bodies on which they are placed
at considerable expense.
Other important Earth mega-problem is efficient transfer of electric energy long distances
(intra-national, international, intercontinental). The consumption of electric energy strongly
depends on time (day or night), weather (hot or cold), from season (summer or winter). But
electric station can operate most efficiently in a permanent base-load generation regime. We
need to transfer the energy a far distance to any region that requires a supply in any given
moment or in the special hydro-accumulator stations. Nowadays, a lot of loss occurs from
such energy transformation. One solution for this macro-problem is to transfer energy from
Europe to the USA during nighttime in Europe and from the USA to Europe when it is night
in the USA. Another solution is efficient energy storage, which allows people the option to
save electric energy.
The storage of a big electric energy can help to solve the problem of cheap space launch.
The problem of an acceleration of a spaceship can be solved by using of a new linear
electrostatic engine suggested in [5]. However, the cheap cable space launch offered by
author [4] requires utilising of gigantic energy in short time period. (It is inevitable for any
launch method because we must accelerate big masses to the very high speed - 8 11 km/s).
But it is impossible to turn off whole state and connect all electric station to one customer.
The offered electric energy storage can help solving this mega-problem for humanity.
OFFERED INNOVATIONS AND BRIEF DESCRIPTIONS
The author offers the series of innovations that may solve the many macro-problems of
transportation energy in space, and the transportation and storage energy within Earth‘s
biosphere. Below are some of them.
(1) transfer of electrical energy in outer space using the conductive cord from plasma.
Author solved the main problem - how to keep plasma cord in compressed form. He
developed theory of space electric transference, made computations that show the
possibility of realization for these ideas with existing technology. The electric energy
may be transferred in hundreds millions of kilometers in space (include Moon and
Mars).
(2) method of construction for space electric lines and electric devices.
(3) method of utilization of the plasma cable electric energy.
(4) a new very perspective gigantic plasma MagSail for use in outer space as well as a
new method for connection the plasma MagSail to spaceship.
(5) a new method of projecting a big electric energy through the Earth's ionosphere.
(6) a new method for storage of a big electric energy used Earth as a gigantic spherical
condenser.
(7) a new propulsion system used longitudinal (cable axis) force of electric currency.
New Concepts, Ideas and Innovations in Aerospace… 125
Below are some succinct descriptions of some constructions made possible by these
revolutionary ideas.
1. Transferring Electric Energy in Space
The electric source (generator, station) is connected to a space apparatus, space station or
other planet by two artificial rare plasma cables (Figure 1a). These cables can be created by
plasma beam [7] sent from the space station or other apparatus.
The plasma beam may be also made the space apparatus from an ultra-cold plasma [7]
when apparatus starting from the source or a special rocket. The plasma cable is selfsupported
in cable form by magnetic field created by electric currency in plasma cable
because the magnetic field produces a magnetic pressure opposed to a gas dynamic plasma
pressure (teta-pinch)(Figure 2). The plasma has a good conductivity (equal silver and more)
and the plasma cable can have a very big cross-section area (up thousands of square meter).
The plasma conductivity does not depend on its density. That way the plasma cable has a no
large resistance although the length of plasma cable is hundreds millions of kilometers. The
needed minimum electric currency from parameters of a plasma cable researched in
theoretical section of this article.
The parallel cables having opposed currency repels one from other (Figure 1a). They also
can be separated by a special plasma reflector as it shown in figs. 1b, 1c. The electric cable of
the plasma transfer can be made circular (Figure 1c).
Figure 1. Long distance plasma transfer electric energy in outer space. a - Parallel plasma transfer, b -
Triangle plasma transfer, c - circle plasma transfer. Notations: 1 - current source (generator), 2 - plasma
wire (cable), 3 - spaceship, orbital station or other energy addresses, 4 - plasma reflector, 5 - central
body.
Figure 2. A plasma cable supported by self-magnetic field. Notations: 1 -plasma cable, 2 - compressing
magnetic field, 3 - electric source, 4 - electric receiver, 5 - electric currency, 6 - back plasma line.
126 Alexander Bolonkin
The radial magnetic force from a circle currency may be balanced electric charges of
circle and control body or/and magnetic field of the space ship or central body (see theoretical
section). The circle form is comfortable for building the big plasma cable lines for spaceship
not having equipment for building own electric lines or before a space launch. We build small
circle and gradually increase the diameter up to requisite value (or up spaceship). The
spaceship connects to line in suitable point. Change the diameter and direction of plasma
circle we support the energy of space apparatus. At any time the spaceship can disconnect
from line and circle line can exist without user.
The electric tension (voltage) in a plasma cable is made two nets in issue electric station
(electric generator) [7]-[8]. The author offers two methods for extraction of energy from the
electric cable (Figure3) by customer (energy addresses). The plasma cable currency has two
flows: electrons (negative) flow and opposed ions (positive) flow in one cable. These flows
create an electric current. (It may be instances when ion flow is stopped and current is
transferred only the electron flow as in a solid metal or by the ions flow as in a liquid
electrolyte. It may be the case when electron-ion flow is moved in same direction but
electrons and ions have different speeds). In the first method the two nets create the opposed
electrostatic field in plasma cable (resistance in the electric cable [7]-[8]) (figs.1, 3b). This
apparatus resistance utilizes the electric energy for the spaceship or space station. In the
second method the charged particles are collected a set of thin films (Figure 3a) and emit
(after utilization in apparatus) back into continued plasma cable (Figure3a)(see also [7]-[8]).
Figure 3. Getting the plasma currency energy from plasma cable. a - getting by two thin conducting
films; b - getting two nets which brake the electric current flux; c - plasma reflector. Notations: 1 -
spaceship or space station, 2 - set (films) for collect (emit) the charged particles, 3 - plasma cable, 4 -
electrostatic nets.
Figure 3c presents the plasma beam reflector [7]-[8]. That has three charged nets. The
first and second nets reflect (for example) positive particles, the second and third nets
reflected the particles having an opposed charge.
New Concepts, Ideas and Innovations in Aerospace… 127
2. Transmitting of the Electric Energy to Satellite, Earth's Space Station, or
Moon
The suggested method can be applied for transferring of electric energy to space satellites
and the Moon. For transmitting energy from Earth we need a space tower of height up 100
km, because the Earth's atmosphere will wash out the plasma cable or we must spend a lot of
energy for plasma support. The design of solid, inflatable, and kinetic space towers are
revealed in [4],[13]-[14],[16].
It is possible this problem may be solved with an air balloon located at 30-45 km altitude
and connected by conventional wire with Earth's electric generator. Further computation can
make clear this possibility.
If transferring valid for one occasion only, that can be made as the straight plasma cable 4
(Figure 4). For multi-applications the elliptic closed-loop plasma cable 6 is better. For
permanent transmission the Earth must have a minimum two space towers (Figure 4). Many
solar panels can be located on Moon and Moon can transfer energy to Earth.
Figure 4. Transferring electric energy from Earth to satellite, Earth's International Space Station or to
Moon (or back) by plasma cable. Notations: 1 - Earth, 2 - Earth's tower 100 km or more, 3 - satellite or
Moon, 4 - plasma cable, 5 - Moon orbit, 6 - plasma cable to Moon, 7 - Moon.
3. Transferring Energy to Mars
The offered method may be applied for transferring energy to Mars including the case
when Mars may be located in opposed place of Sun (Figure 5). The computed macroproject is
in Macroprojects section.
4. Plasma AB Magnetic Sail
Very interesting idea to build a gigantic plasma circle and use it as a Magnetic Sail
(Figure 6) harnessing the Solar Wind. The computations show (see section "Macroproject")
that the electric resistance of plasma cable is small and the big magnetic energy of plasma
128 Alexander Bolonkin
circle is enough for existence of a working circle in some years without external support. The
connection of spaceship to plasma is also very easy. The space ship create own magnetic field
and attracts to MagSail circle (if spacecraft is located behind the ring) or repels from MagSail
circle (if spaceship located ahead of the ring). The control (turning of plasma circle) is also
relatively easy. By moving the spaceship along the circle plate, we then create the asymmetric
force and turning the circle. This easy method of building the any size plasma circle was
discussed above.
Figure 5. Transferring of electric energy from Earth to Mars located in opposed side of Sun.
Notations: 1 - Sun, 2 - Earth, 3 - Mars, 4 - circle plasma cable.
Figure 6. Plasma AB-MarSail. Notations: 1 - spaceship, 2 - plasma ring (circle), 3 - Solar wind, 4 -
MagSail thrust, 5 - magnetic force of spaceship.
5. Wireless Transferring of Electric Energy in Earth
It is interesting the idea of energy transfer from one Earth continent to another continent
without wires. As it is known the resistance of infinity (very large) conducting medium does
not depend from distance. That is widely using in communication. The sender and receiver
are connected by only one wire, the other wire is Earth. The author offers to use the Earth's
ionosphere as the second plasma cable. It is known the Earth has the first ionosphere layer E
at altitude about 100 km (Figure 7). The concentration of electrons in this layer reaches 5104
New Concepts, Ideas and Innovations in Aerospace… 129
1/cm3
in daytime and 3.1103
1/cm3
at night (Figure 7). This layer can be used as a
conducting medium for transfer electric energy and communication in any point of the Earth.
We need minimum two space 100 km. towers (Figure 8). The cheap optimal inflatable,
kinetic, and solid space towers are offered and researched by author in [4], [6], [7], [16].
Additional innovations are a large inflatable conducting balloon at the end of the tower and
big conducting plates in a sea (ocean) that would dramatically decrease the contact resistance
of the electric system and conducting medium.
Theory and computation of these ideas are presented in Macroprojects section.
Figure 7. Consentration/cm3 of electrons (= ions) in Earth's atmosphere and layers of ionosphere (see
also Figure 8 , Ch. 2 A).
Figure 8. Using the ionosphere as conducting medium for transferring a huge electric energy between
continents and as a large storage of the electric energy. Notations: 1 - Earth, 2 - space tower about 100
km of height, 3 - conducting E layer of Earth's ionosphere, 4 - back connection through Earth.
130 Alexander Bolonkin
THEORY OF SPACE PLASMA TRANSFER FOR ELECTRIC ENERGY,
ESTIMATIONS AND COMPUTATIONS
1. General Theory
The magnetic intensity and magnetic pressure of straight electric currency has maximum
on surface of plasma cable. Let us to equate plasma gas pressure to a magnetic pressure and
find the request equilibrium electric currency for same temperature of electrons and ions
,
2
, 4 ,
,
2
,
2
2 ,
2
0.5
0
2
0
k
m u
T
knT
P P I r
r
I
H
H
P nkT P
e e
k
k
m g
g k m
(1)
where Pg is plasma gas pressure, N/m2
; Pm is magnetic pressure, N/m2
; n is plasma density,
1/m
3
; k = 1.3810-23 is Boltzmann coefficient, J/K; 0 = 410-7
is magnetic constant, G/m; H
is magnetic intensity, A/m; I is electric currency, A; r is radius of plasma cable, m; Tk
is
plasma temperature, K; me = 9.1110-31 is electron mass, kg; ue
is electron speed, m/s.
From relation for the currency we have a current electron speed u relative ions along
cable axis
e
e
u
nm
enS
r
enS
I
u
0.5
2 0
4
(2)
where S = r
2
is cross-section area of plasma cable, m2
.
The mass of ion is more the mass of electron in thousands times and we assume u = ue
in
(2) after some collisions. From this condition we find the relation between r and n
n n
m
e
r
e
7
0
2 2 1 1.510
(3)
The computation (2) is presented in Figure 9.
Specific plasma resistance and usual resistance of cable can be computed by equations:
1.03 10 ln m, / ,
4 3/ 2
Z T R ρl S
(4)
where is specific plasma resistance,
.m; Z is ion charge state, ln 515 10 is
Coulomb logarithm; T = Tkk/e = 0.8710-4
Tk
is plasma temperature in eV; e = 1.610-19 is
electron charge, C; R is electric resistance of plasma cable , ; l is plasma cable length, m; S
is the cross-section area of the plasma cable , m2
.
New Concepts, Ideas and Innovations in Aerospace… 131
Figure 9. Equilibrium radius of plasma cable via plasma density.
The computation of specific resistance of plasma cable is presented in Figure 10.
The requested a minimum voltage, power, the transmitter power and coefficient of
electric efficiency are:
Um
IR, Wm
IUm
, U Um
U, W IU, 1Wm
/W
(5)
where Um, Wm are requested minimal voltage, [V], and power, [W], respectively; U is used
voltage, V; U is electric voltage over minimum voltage, V; W is used electric power, W; is
coefficient efficiency of the electric line.
Figure 10. Specific plasma resistance .m of equilibrium plasma cable versus electric currency, A.
132 Alexander Bolonkin
The computation of mentioned over values are presented in Figures 11 13. As you can
see we can transfer the electric power of millions watts in outer space with very high
efficiency, better than in Earth.
Figure 11. Requested minimum electric tension via the equilibrium plasma cable radius for different
electric currency and for distance 100 millions kilometers.
Figure 12. Transferred electric power (millions W) via voltage over minimum electric tension (see
requested minimum tension in Figure10) for different electric currency, distance 100 millions of
kilometers and radius of plasma cable 50 m.
New Concepts, Ideas and Innovations in Aerospace… 133
Figure 13. Coefficient efficiency of the electric transfer via over electric tension for different electric
currency, distance 100 millions of kilometers and radius of plasma cable 50 m.
The equilibrium mass M [kg] of plasma cable is
, 2.25 10 / , 2.25 10 ,
2 1 4 1 4 M lSnm S r n M m l
i
p
(6)
where mi
is ion mass of plasma, kg; = mi
/mp is relative mass of ion; mp = 1.6710-27 is mass
of proton, kg. Look your attention - the equilibrium mass of plasma cable does not depend
from radius and density of plasma cable.
Computations are presented in Figure 14. The double plasma cable for Jupiter (distance is
770 millions km) made from hydrogen H2 (mu = 2) has mass only 3 kg. That means the mass
of plasma cable is closed to zero.
Figure 14. Mass of plasma cable versus the cable length and a relative mass of ion.
134 Alexander Bolonkin
2. Circle Plasma Cable
The force acting in a circle particle (proton) moved in electric and magnetic fields may be
computed by equations
2
0
0
2 3
2
1
4
. ,
R
eQ
F ev B F
R
m v
F
p
(7)
where F1, F2, F3 are centrifugal, Lawrence, and electrostatic forces respectively (all vectors),
N; mp = 1.6710-27 kg mass of proton; v - speed of particle, m/s; e - electron (proton) charge;
B - total magnetic induction (magnetic field strength), T; Q0 - charge of central body, C; o =
8.8510-12 F/m - electric constant.
The equilibrium condition is
0
i
Fi
(8)
3. Electric Pressure from the Plasma Cable
The plasma has pressure in plasma cable. This pressure is small, but the cable can has a
large diameter (up 200 m or more) and this pressure acting a long time can accelerate or brake
the space apparatus. Electric pressure P can be computed by equations
0 2
2
0
4
, 2
2
,
2
P P S I
r
I
H
H
Pm m
(9)
Estimation. For I = 104 A the electric pressure equals 10 N, for I = 105 A one equals 1000
N. In reality the electric pressure may be significantly more because the kinetic pressure
along cable axis may be more then plasma pressure into plasma cable (see below).
4. Additional Power from a Space Apparatus Motion
This power is
W PV
(10)
where V is apparatus speed, m/s.
Estimation. For V = 11 km/s, I = 103 A, this power equals 550 W, for I = 105
the power
equals 55000 W. We spend this power when space apparatus move off from the energy
source and receive it when apparatus approach to the energy station.
New Concepts, Ideas and Innovations in Aerospace… 135
5. Track Length of Plasma Electrons and Ions
The track length L and the track time of particles is
L T
/, 1/
(11)
where T is particle velocity, cm/s; is particle collision rate, 1/s.
The electron and ion collision rate are respectively:
8 4 1/ 2 3/ 2 1
5 3/ 2 1
4.80 10 ln
2.91 10 ln
Z n T s
n T s
i i i
e e e
(12)
where Z is ion charge state, ln 515 10 is Coulomb logarithm, = mi
/mp is relative
mass of ion; mp = 1.6710-27 is mass of proton, kg; n is density of electrons and ions
respectively; T is temperature of electron and ion respectively, eV.
Electron and ion terminal velocity are respectively:
( / ) 9.79 10 cm/s
( / ) 4.19 10 cm/s
1/ 2 7 1/ 2 1/ 2
1/ 2 7 1/ 2
Ti i i i
Te e e e
k T m T
k T m T
(13)
Substitute equations (12)-(13) in (11) we receive
2.04 10 / ln cm,
1.44 10 / ln cm,
13 2 4
13 2
i e e
e e e
L T Z n
L T n
(14)
Estimation. For electron having n = 105
1/cm3
, T = 100 eV, ln 10 we get L = 2106
km, 300 s.
That means the plasma electrons have very few collusions, small dispersion, and it can
have different average ELECTRON (relative ions) temperature along cable axis and
perpendicular cable axis. It is not surprise because plasma can have different average
temperature of electron and ions. That also means that our assumption about same terminal
and currency electron velocities is very limited and parameters of plasma electric system will
many better, then in our computation. The plasma in our system may be very cooled in radial
direction and hot in axial direction. That decreases an electric currency needed for plasma
compression and allows to transfer a plasma beam, energy, and thrust at long distance.
6. Long Distance Wireless Transfer of Electricity in Earth
The transferring electric energy from one continent to other continent through ionosphere
and Earth surface is described over. For this transferring we need two space towers of 100 km
height, The towers must have a big conducting ball at top end and underground (better
136 Alexander Bolonkin
underwater) plates for decreasing the contact electric resistance. The contacting ball is large
(up to 100 200 m diameter) inflatable gas balloon having the conductivity layer (covering).
Let us to offer the method which allows computation the parameters and possibilities this
electric line.
The electric resistance and other values for big conductivity medium can be estimated by
equations:
a
U W IU a U E
I a
U
R
a
2
, 2 ,
2
1 2
(15)
where R is electric resistance of big conductivity medium, (for sea water = 0.3
.m); a is
radius of contacting balloon, m; is electric conductivity, (
.m)-1
; Ea is electric intensity on
the balloon surface, V/m.
The conductivity of E-layer of Earth's ionosphere as the rare ionized gas can be
estimated by equations:
e
k
m
k
e m
kT
v
r p
kT
L
v
L
m
ne
8
,
2
, where ,
2
2
2
(16)
where n = 3.1109
51011 1/m3
is density of free electrons in E-layer of Earth's ionosphere,
1/m3
; is a track time of electrons, s; L is track length of electrons, m; v is average electron
velocity, m/s; rm = 3.710-10 (for hydrogen N2) is diameter pf gas molecule, m; p = 3.210-3
N/m2
is gas pressure for altitude 100 km, N/m2
; me = 9.1110-31 is mass of electrons, kg.
The transfer power and efficiency are
W IU, 1 R
c
/ R
(17)
where Rc
is common electric resistance of conductivity medium, ; R is total resistance of the
electric system, .
See the detail computations in Macro-Projects section.
7. Earth's Ionosphere as the Gigantic Storage of Electric Energy
The Earth surface and Earth's ionosphere is gigantic spherical condenser. The electric
capacitance and electric energy storied in this condenser can be estimated by equations:
2
4 ,
1/ 1/( )
4
2 2
0
0
0 0
0 CU E
H
R
R R H
C
(18)
where C is capacity of condenser, C; R0 = 6.369106 m is radius of Earth; H is altitude of Elayer,
m; o = 8.8510-12 F/m is electrostatic constant; E is electric energy, J.
New Concepts, Ideas and Innovations in Aerospace… 137
The leakage currency is
a
a
a a a
a
t CR
R
H
U n e R
H
R
i
,
4
, ,
3
2
0
2
0
(19)
where i leakage currency, A; a is conductivity of Earth atmosphere, (
.m)-1
, na is free
electron density of atmosphere, 1/m3
; = 1.310-4
(for N2) is ion mobility, m2
/(sV); Ra is
Earth's atmosphere resistance, ; t is time of discharging in e = 2.73 times, s;
8. Magnetic Sail
Circle plasma cable allows creating the gigantic Magnetic Sail. This sail has drag into
Solar wind, which can be used as a thrust of a space ship. The electric resistance of plasma
MagSail is small and MagSail can exist some years. That is also big good storage of electric
energy. Space ship connects to MagSail by magnetic force.
The energy storage in plasma ring is
2
, where
2
0
2 R
L
L I
E R
R
R
(20)
where ER is energy in magnetic ring, J [15]; LR is inductance of magnetic ring, H; R is radius
of magnetic ring, m.
The ring spends power
m m m m U R I, W IU
(21)
The existing time is
m
R
R W
E
c
(22)
where cR is part of ring energy spent in life time, s (0 < cR < 1).
The ring energy is enough for some years of ring existing.
See the estimations in Projects section.
MACROPROJECTS
The macroprojects discussed below are not optimal. These are only examples of
estimations: what parameters of system we can have.
1. Space Electric Line the Length in 100 Millions of km
Let us take the following date of the electric line: radius of plasma cable is r = 150 m,
(cross-section of plasma cable equals S = r
2
= 7.06104
m
2
), plasma density is n = 1010
1/m3
, electric currency is I = 100 A, electric voltage is U = 2106 V. Use the equations (1)-(6)
we are receiving:
Electron velocity is u = I/enS = 8.85105 m/s, electron temperature in eV is T = 2.23 eV,
electron temperature in K is Tk = 2.59104 K, specific electric resistance is = 310-4
.m,
Coulomb logarithm is ln = 10, charge state is Z = 1, electric resistance is R =2L/S =
138 Alexander Bolonkin
8.8102 , loss voltage is Um = IR = 8.8104 V, loss power is Wm = IUm = 8.8106 W,
transfer power is W = IU = 2108 W, coefficient efficiency is = 0.956.
As you see, our system can transmit 200 million watts of power at distance 100 million
kilometers with efficiency 95.6%. I remind that the minimal distance to Mars is only about 60
million of kilometers.
Mass of our plasma line from hydrogen H2 is only 470 g.
2. Transferring Electric Energy to Moon or Back
Let us take the initial data: radius of plasma cable r = 15 m (S = r
2
= 706 m2
), plasma
density n = 1012 1/m3
, electric currency I = 1000 A, distance 385,000 km.
Then: u = I/enS = 8.85106 m/s, T = 223 eV, Tk = 2.59106 K, = 3.110-7
.m, ln =
10, Z = 1, R =2L/S = 3.410-1 , Um = IR = 3.4102 V, Wm = IUm = 3.4105 W.
If voltage is U = 3.4103 V, then transmitting power is W = IU = 3.4108 W, coefficient
efficiency is = 0.9.
If U = 3.4104 V, then W = IU = 3410
8 W, = 0.99.
As you see, this system can transmit 340 3400 million watts of power to Moon at
distance 385,000 kilometers with efficiency 90 99%.
If we take electric currency I = 100 A and voltage U = 3.4103 V, then the transfer
energy is W = IU = 3.4107 W, = 0.9. The same parameters are transfer energy to Earth's
Space Station. Now the International Space Station has only electric power W = 104 W.
3. Transferring Energy to Mars
Located beyond the in Sun opposed on Earth side. In this case we use the circle plasma
transfer (Figure 5).
Let us take the following initial data: Radius of circle R = 1.91011 m = 190 millions
kilometers (Length of circle equals L 121011 m), r = 150 m (S = r
2
= 7.06104
m
2
), n =
1010 1/m3
, I = 100 A, U = 107 V.
Then: u = I/enS = 8.85105 m/s, T = 2.23 eV, Tk = 2.59104 K, = 3.110-4
.m, ln =
10, Z = 1, R =L/S = 5.27103 , Um = IR = 5.27105 V, Wm = IUm = 5.27107 W, W = IU =
2108 W, 0.95.
Mass of our plasma line from hydrogen H2 is only about 3 kg.
4. Plasma Magnetic Sail (Figure 6)
Let us take the following initial data: radius of MagSail R = 5104 m = 50 km, r =
1.5103 m (S = r
2
= 7.06106
m
2
), n = 108
1/m3
, I = 104 A.
Then: u = I/enS = 8.85107 m/s, T = 2.23104
eV, Tk = 2.59108 K, = 3.110-10
.m, ln
= 10, Z = 1, Rm =L/S = 1.3810-11 , Um = IR = 1.3810-7 V, Wm = IUm = 1.410-3 W.
If U = 100 V, the ring energy is E = 5106
J [15]. If we spent only 10% of the ring
energy, our MagSail will work about 10 years.
The gigantic plasma space MagSail is also an excellent storige of electric energy. If we
take U = 105 V, the ring will keep about E = 5109
J.
New Concepts, Ideas and Innovations in Aerospace… 139
5. Wireless Transferring Energy between Earth's Continents (Figure 7).
Let us take the following initial data: Gas pressure at altitude 100 km is p = 3.210-3
N/m2
, temperature is 209 K, diameter nitrogen N2 molecule is 3.710-10 m, the ion/electron
density in ionosphere is n = 1010 1/m3
, radius of the conductivity inflatable balloon at top the
space tower (mast) is a = 100 m (contact area is S = 1.3105
m
2
), specific electric resistance
of a sea water is 0.3
.m, area of the contact sea plate is 1.3103
m
2
.
The computation used equation (15)-(19) give: electron track in ionosphere is L = 1.5 m,
electron velocity = 9104 m/s, track time = 1.6710
-5
s, specific resistance of ionosphere
is = 4.6810-3
(
.m)-1
, contact resistance of top ball (balloon) is R1 = 0.34 , contact
resistance of the lower sea plates is R2 = 4.810-3 , electric intensity on ball surface is 5104
V/m.
If the voltage is U = 107 V, total resistance of electric system is R = 100 , then electric
currency is I = 105 A, transferring power is W= IU = 1012 W, coefficient efficiency is 99.66%.
In practice we are not limited in transferring any energy in any Earth's point having the 100
km space mast and further transfer by ground-based electric lines in any geographical region
of radius 1000 2000 km.
6. Earth's Ionosphere as the Storage Electric Energy
It is using the equations (18)-(19) we find the Earth's-ionosphere capacity C = 4.510-2 C.
If U = 108 V, the storage energy is E = 0.5CU2
= 2.251014 J. That is large energy.
Let us now estimate the leakage of current. Cosmic rays and Earth's radioactivity create
1.5 10.4 ions every second in 1 cm3
. But they quickly recombine in neutral molecule and
the ions concentration is small. We take the ion concentration of lower atmosphere n = 106
1/m3
. Then the specific conductivity of Earth's atmosphere is 2.110-17 (
.m)-1
. The leakage
currency is i = 10-7
U. The altitude of E-layer is 100 km. We take a thickness of atmosphere
only 10 km. Then the conductivity of Earth's atmosphere is 10-24 (
.m)-1
, resistance is Ra =
1024 , the leakage time (decreasing of energy in e = 2.73 times) is 1.5105
years.
As you can clearly see the Earth's ionosphere may become a gigantic storage site of
electricity.
DISCUSSION
The offered ideas and innovations may create a jump in space and energy industries.
Author has made initial base research that conclusively show the big industrial possibilities
offered by the methods and installations proposed. Further research and testing are necessary.
As that is in science, the obstacles can slow, even stop, applications of these revolutionary
innovations. For example, the plasma cable may be unstable. The instability mega-problem of
a plasma cable was found in tokomak RandD, but it is successfully solved at the present time.
The same method (rotation of plasma cable) can be applied in our case.
CONCLUSION
This new revolutionary idea - wireless transferring of electric energy in the hard vacuum
of outer space is offered and researched. A rare plasma power cord as electric cable (wire) is
140 Alexander Bolonkin
used for it. It is shown that a certain minimal electric currency creates a compressed force that
supports the plasma cable in the compacted form. Large amounts of energy can be transferred
hundreds of millions of kilometers by this method. The requisite mass of plasma cable is
merely hundreds of grams. It is computed that the macroprojects: transferring of hundreds of
kilowatts of energy to Earth's International Space Station, transfer energy to Moon or back,
transferring energy to a spaceship at distance of hundreds of millions of kilometers, transfer
energy to Mars when wirelessly. The transfer of colossal energy from one continent to
another continent (for example, Europe to USA and back), using the Earth‘s ionosphere as a
gigantic storage of electric energy, using the plasma ring as huge MagSail for moving of
spaceships. It is also shown that electric currency in plasma cord can accelerate or slow
various kinds of outer space apparatus.
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: Bolonkin, and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Bolonkin, A.A., Getting of Electric Energy from Space and Installation for It, Russian
patent application #3638699/25 126303, 19 August, 1983 (in Russian), Russian PTO.
[2] Bolonkin, A. A., Method of Transformation of Plasma Energy in Electric Current and
Installation for It. Russian patent application #3647344 136681 of 27 July 1983 (in
Russian), Russian PTO.
[3] Bolonkin, A. A., Transformation of Energy of Rarefaction Plasma in Electric Current
and Installation for it. Russian patent application #3663911/25 159775, 23 November
1983 (in Russian), Russian PTO.
[4] Bolonkin A.A., Non-Rocket Space Launch and Flight, Elsevier, London, 2006, 488 ps.
[5] Bolonkin A.A., Micro-Thermonuclear AB-Reactors, AIAA-2006-8104, 14th Space
Planes and Hypersonic System Conference, 6-9 November, 2006, Australia. Under
publication.
[6] Bolonkin A.A., Utilization of Wind Energy at High Altitude, AIAA Conference
Guidance, Navigation, and Control, Rhode Island, 16-19 August, 2004, AIAA-2004-
5705. Under publication.
[7] Bolonkin A.A., Beam Space Propulsion, AIAA-2006-7492, Conference Space-2006,
18-21 Sept;, 2006, San Jose, CA, USA.
[8] Bolonkin A.A., Electrostatic AB-Ramjet Space Propulsion, AIAA/AAS Astrodynamics
Specialist Conference, 21-24 August 2006, USA. AIAA-2006-6173.
[9] Bolonkin A.A., Electrostatic Linear Engine, AIAA-2006-5229, 42nd Joint Propulsion
Conference, 9-12 June 2006, Sacramento, USA.
[10] Bolonkin A.A., High-Speed Solar Sail, AIAA-2006-4806, 42nd Joint Propulsion
Conference, 9-12 June 2006, Sacramento, USA.
[11] Bolonkin A.A., A New Method of Atmospheric Reentry for Space Shuttle, AIAA-2006-
6985, MAO Conference, 6-9 Sept. 2006, USA.
[12] Bolonkin A.A., Suspended Air Surveillance System, AIAA-2006-6511, AFM
Conference, 21-29 Aug. 2006, Keystone, USA.
New Concepts, Ideas and Innovations in Aerospace… 141
[13] Bolonkin A.A., Optimal Inflatable Space Tower with 3-100 km Height, Journal of the
British Interplanetary Society, Vol.56, No. 3/4, 2003, pp.97-107.
[14] Bolonkin A.A., Optimal Solid Space Tower, AIAA-2006-7717. ATIO Conference, 25-
27 Sept. 2006, Wichita, Kansas, USA.
[15] Bolonkin A.A., Theory of Space Magnetic Sail Some Common Mistakes and
Electrostatic MagSail. Presented as paper AIAA-2006-8148 to 14-th Space Planes and
Hypersonic System Conference, 6-9 November 2006, Australia.
[16] Macro-Engineering - A challenge for the future. Collection of articles. Eds. V. Badescu,
R. Cathcart and R. Schuiling, Springer, 2006.
New Concepts, Ideas and Innovations in Aerospace…
Attachment to Part A, Ch. 6. Possible forms of Space Ships
New Concepts, Ideas and Innovations in Aerospace…
Chapter 7
SIMPLEST AB-THERMONUCLEAR SPACE
PROPULSION AND ELECTRIC GENERATOR*
ABSTRACT
The author applies, develops and researches mini-sized Micro- AB Thermonuclear
Reactors for space propulsion and space power systems. These small engines directly
convert the high speed charged particles produced in the thermonuclear reactor into
vehicle thrust or vehicle electricity with maximum efficiency. The simplest ABthermonuclear
propulsion offered allows spaceships to reach speeds of 20,000 - 50,000
km/s (1/6 of light speed) for fuel ratio 0.1 and produces a huge amount of useful electric
energy. Offered propulsion system permits flight to any planet of our Solar system in
short time and to the nearest non-Sun stars by E-being or intellectual robots during a
single human life period.
Keywords: AB-propulsion, thermonuclear propulsion, space propulsion, thermonuclear
power system.
INTRODUCTION
At present, both solid and liquid chemical fueled rockets are used for launch to and
flights in interplanetary outer space. They have been intensively developed since War II when
German engineer Wernher von Braun (1912-1977) successfully designed the first long
distance rocket FAU-2. In the subsequent years, liquid and solid rockets reached their
developmental peak. Their main shortcomings are (1) very high space launch cost of $20,000
– 50,000/kg; (2) large fuel consumption; (3) liquid fuel storage problems because oxidizer
and fuel (for example; oxygen and hydrogen) require cryogenic temperatures, or they are
poisonous substances (for example; nitric acid, N2O3).
In past years, the author and other scientists have published series of new methods that
promise to revolutionize space launch and space flight [1-14]. These include cable
accelerator, circle launcher and space keeper, space elevator transport system, space towers,
kinetic towers, the gas-tube method, sling rotary method, electromagnetic and electrostatic
accelerators, tether system, Earth-Moon or Earth-Mars non-rocket cable transport system.
There include new propulsion and power systems such as solar and magnetic sails, Solar
wind sail, radioisotope sail, electrostatic space sail, laser beam, kinetic anti-gravitator, multi-
-------------------
* This work presented as Bolonkin‘s paper AIAA-2007-4613 to 38th AIAA Plasmadynamics and Lasers
Conference in conjunction with the16th International Conference on MHD Energy Conversion on 25-27
June 2007, Miami, USA. See also http://arxiv.org search "Bolonkin".
146 Alexander Bolonkin
reflective beam propulsion system, asteroid employment electrostatic levitation, etc. (Too,
there are new ideas in aviation that can be useful for flights in the atmosphere.)
Some of these have the potential to decrease space launch costs thousands of times,
others allow changing the speed and direction of space apparatus without expending fuel.
The thermonuclear propulsion and power method is very perspective -- though not
speculative -- because it promises high vehicular apparatus speed up 50,000 km/s. This
method needs a small, special thermonuclear reactor that will allow the direct and efficient
utilization of the kinetic energy of nuclear particles – the AB Thermonuclear Reactor –first
offered by author [15].
DESCRIPTION OF INNOVATIONS
The AB thermonuclear propulsion and electric generator are presented in Figure 1. As it
is shown in [15] the minimized, or micro-thermonuclear reactor 1 generates high-speed
charged particles 2 and neutrons that leave the reactor. The emitted charged particles may be
reflected by electrostatic reflector, 4, or adsorbed by a semi-spherical screen 3; the neutrons
may only be adsorbed by screen 3.
In screen of the AB-thermonuclear reactor (Figure 1a) the forward semi-spherical screen
3 adsorbed particles that move forward. The particles, 2, of the back semi-sphere move freely
and produce the vehicle‘s thrust. The forwarded particles may to warm one side of the screen
(the other side is heat protected) and emit photons that then create additional thrust for the
apparatus. That is the photon AB-thermonuclear thruster.
In reflector AB-thermonuclear reactor (Figure 1b) the neutrons fly to space, the charged
particles 5 are reflected the electrostatic reflector 4 to the side opposed an apparatus moving
and create thrust.
The screen-reflector AB-thermonuclear reactor (Figure1c) has the screen and reflector.
The spherical AB-propulsion-generator (Figure 1d) has two nets which stop the charged
particles and produced electricity same as in [14] Chapter 17. Any part 8 of the sphere may be
cut-off from voltage and particles 9 can leave the sphere through this section and, thusly,
create the thrust. We can change direction of thrust without turning the whole apparatus.
Figure 1. Types of the suggested propulsion and power system. (a) screen ABthermonuclear
propulsion and photon AB-thermonuclear propulsion ; (b) (electrostatic)
New Concepts, Ideas and Innovations in Aerospace… 147
reflector AB-thermonuclear propulsion; (c) screen-reflector AB-thermonuclear propulsion;
(d) spherical AB-propulsion-generator. Notations: 1 - micro (mini) AB-thermonuclear reactor
[15], 2 - particles (charged particles and neutrons) , 3 - screen for particles, 4 - electrostatic
reflector; 5 - charged particles, 6 - neutrons, 7 - spherical net of electric generator, 8 -
transparency (for charged particles) part of spherical net, 9 - charged particle are producing
the thrust, 10 - electron discharger, 11 - photon radiation.
THEORY OF THE THERMONUCLEAR REACTOR,
PROPULSION AND POWER
List of Main Equations
Below are the main equations for the proper estimation of benefits from the offered
innovations.
1. Energy needed to overcome the Coulomb barrier
r A
r
k Z Z e
E Fdr E
r
Q Q
F k
r
15
0
0
2
1 2
2
1 2
(1.2 1.5) 10
, , ,
0
(1)
where k = 1.3810-23 Boltzmann constant, J/oK; Z1, Z2 are charge state of 1 and 2 particles
respectively; e = 1,610-19 C is charge of electron; ro is radius of nuclear force, m; A is
number of element; F is force, N; E is energy, J; Q is charge of particles.
For example, for reaction H+H (hydrogen, Z1 = Z2 =1, ro 210-15 m) this energy is 0.7
MeV or 0.35 MeV for every particle. The real energy is about 30 times less because some
particles have more than average speed and there is a tunnel effect.
2. Energy needed for ignition. Figure 8 [15] shows a magnitude n (analog of Lawson
criterion) required for ignition.
Present-day industry produces powerful lasers:
• Carbon dioxide lasers emit up to 100 kW at 9.6 µm and 10.6 µm, and are used in
industry for cutting and welding.
• Carbon monoxide lasers must be cooled, but can produce up to 500 kW.
Special laser and ICF reactors:
• NOVA (1999, USA). Laser 100 kJ (wavelenght =105410-9 m) and 40 kJ
(wavelenght = 35110-9 m), power few tens of terawatts (1 TW = 1012 W), time of
impulse (2 4) 10-9
s, 10-beams, matter is Nd:class.
• OMERA (1995, USA). 60-beam, neodyminm class laser, 30 kJ, power 60 TW.
148 Alexander Bolonkin
• Z-machine (USA, under construction), power is up 350 TW. It can create currency
impulses up to 20106 A.
• NIF (USA). By 2005, the National Ignition Facility is worked on a system that, when
complete, will contain 192-beam, 1.8-megajoule, 700-terawatt laser system adjoining
a 10-meter-diameter target chamber.
• 1.25 PW - world's most powerful laser (claimed on 23 May 1996 by Lawrence
Livermore Laboratory).
3. Radiation energy from hot solid black body is (Stefan-Boltzmann Law):
4 E T
(2)
where E is emitted energy, W/m2
; = 5.6710-8
- Stefan-Boltzmann constant, W/m2 oK
4
; T is
temperature in oK.
4. Wavelength corresponded of maximum energy density (Wien's Law) is
0
0
2
,
T
b
(3)
where b = 2.897810-3
is constant, m oK; T is temperature, oK; is angle frequency of wave,
rad/s.
5. Pressure for one full reflection is
F 2E / c
(4)
where F - pressure, N/m2
; c = 3108
is light speed, m/s, E is radiation power, W/m2
. If plasma
does not reflect radiation the pressure equals
F = E/c (5)
6. Pressure for plasma multi-reflection [8, 14] is
c q
E
F
1
2 2
(6)
where q is plasma reflection coefficient. For example, if q = 0.98 the radiation pressure
increases by 100 times. We neglect losses of prism reflection.
7. The Bremsstrahlung (brake) loss energy of plasma by radiation is (T > 106 oK)
PB r ne T Zeff Zeff Z nz ne 5.34 10 , where ( )/
3 7 2 0.5 2
(7)
where PBr is power of Bremsstrahlung radiation, W/m3
; ne
is number of particles in m3
; T is a
plasma temperature, KeV; Z is charge state; Zeff is cross-section coefficient for multi-charges
ions. For reactions H+D, D+T the Zeff equals 1.
New Concepts, Ideas and Innovations in Aerospace… 149
Losses may be very high. For some reactions, they are more then useful nuclear energy
and fusion nuclear reaction may be stopped. The Bremsstrahlung emission has continuous
spectra.
8. Electron frequency in plasma is
in "cgs" units, or 56.4( ) in CI units
, or 5.64 10 ( )
4
1/ 4
4 1/ 4
1/ 4
2
n
n
m
n e
pe
pe e
e
e
pe
(8)
where pe is electron frequency, rad/s; ne
is electron density, [1/cm3
]; n is electron density,
[1/m3
]; me = 9.1110-28 is mass of electron, g; e = 1.610-19 is electron charge, C.
The plasma is reflected an electromagnet radiation if frequency of electromagnet
radiation is less then electron frequency in plasma, < pe. That reflectivity is high. For T >
15106 oK it is more than silver and increases with plasma temperature as T
3/2. The frequency
of laser beam and Bremsstrahlung emission are less then electron frequency in plasma.
9. The deep of penetration of outer radiation into plasma is
5 1/ 2
5.31 10
e
pe
p n
c
d
[cm]
(9)
For plasma density ne = 1022 1/cm3
dp = 5.3110-6
cm.
10. The gas (plasma) dynamic pressure, pk
, is
pk nk(Te Ti
) if Te
Tk
then pk 2nkT
(10)
where k = 1.3810-23 is Boltzmann constant; Te
is temperature of electrons, oK; Ti
is
temperature of ions, oK. These temperatures may be different; n is plasma density, 1/m3
; pk
is
plasma pressure, N/m2
.
11. The gas (plasma) ion pressure, p, is
p n k T
3
2
(11)
Here n is plasma density in 1/m3
.
12. The magnetic pm and electrostatic pressure, ps
, are
2
0
0
2
2
1
,
2
m ps
ES
B
p
,
(12)
where B is electromagnetic induction, Tesla; 0 = 410-7
electromagnetic constant; 0 =
8.8510-12 , F/m, is electrostatic constant; ES is electrostatic intensity, V/m.
13. Ion thermal velocity is
150 Alexander Bolonkin
9.79 10 cm/s 5 1/ 2 1/ 2
1/ 2
i
i
i
Ti T
m
k T
v
,
(13)
where = mi /mp , mi
is mass of ion, kg; mp = 1.6710-27 is mass of proton, kg.
14. Transverse Spitzer plasma resistance
c m
T
0.1Z
1.03 10 ln , c m or 3/2
2 3/ 2
Z T
(14)
where ln = 5 15 10 is Coulomb logarithm, Z is charge state.
15. Reaction rates <v> (in cm3
s
-1
) averaged over Maxwellian distributions for low
energy (T < 25 keV) may be represent by
( ) 3.68 10 exp( 19.94 ) cm s ,
( ) 2.33 10 exp( 18.76 ) cm s ,
12 2 / 3 1/ 3 3 1
14 2 / 3 1/ 3 3 1
T T
T T
DT
DD
(15)
where T is measured in keV.
16. The power density released in the form of charged particles is [19]
12 3
13 3
13 2 3
2.9 10 ( ) , W cm
5.6 10 ( ) , W cm
3.3 10 ( ) , W cm
3 3 3
DHe D He DHe
DT D T DT
DD D DD
P n n
P n n
P n
(16)
Here in PDD equation it is included D + T reaction.
RESULTS OF COMPUTATION
1. Some thermonuclear reactions. The primary nuclear reaction is D-D reaction that takes
place when two nuclei of deuterium collide. Deuterium can be obtained from seawater, its
abundance being about 0.0148% that of hydrogen, and used as a fuel resource, this amount
can be regarded as almost inexhaustible.
The D-D reaction consists of the following two reactions:
D+D 3He + n +3.27 MeV, 50% (17)
D+D T + H +4.03 MeV . 50% (18)
In reaction (17) an isotope of helium (3He) and neutron (n) are produced by the collision
of two deuterium nuclei (D). In reaction (2), a tritium (T) and a proton (H) are produced. The
numbers on the right-side denote the kinetic energy released by the reaction, which can be
calculated us follows: If we denote the mass defect of each particle in the unit of MeV (106
eV), we have D: 13.1359 MeV, He: 14.9313 MeV, and n: 8.0714 MeV ([18], p. 1295), so that
the energy released by reaction (17) is
New Concepts, Ideas and Innovations in Aerospace… 151
2 13.1359 - (14.9313 + 8.0714) = 3.2691 = 3.27 MeV.
For reaction (18), we can use for T: 14.9500 MeV and for H: 7.289 MeV.
The partition of the released energy from the reaction products can be estimated from
energy and momentum conservation. Kinetic energy of D before collision is very small
compared to the energy released by the reaction. We can ignore the initial kinetic energy and
treat the deuterium nuclei as being at rest. Denoting the mass and speed of helium and n by 1
and 2 respectively, we have for reaction (17)
1 1 2 2
2
2 2
2
0.5m1
v1 0.5m V E 3.27 MeV, m v m v
(19)
where in the second formula we assumed that He and n fly out in opposite directions. From
these relations, we find
2.45 MeV
2 1 /
1
0.82 MeV,
2 1 /
1
2 1
2
2 2 2
1 2
2
1 1 1
m m
E
E m v
m m
E
E m v
(20)
Obviously, the lighter particle acquires more energy than the heavier particle.
Current nuclear fusion research is focused on the D + T thermonuclear fusion reaction
D + T 4He (3.5 MeV) + n (14.1 MeV), (21)
Reaction (21) can occur in high-temperature deuterium-tritium plasma. Most energy
released by the reaction is converted to the kinetic energy of the neutron. Since the neutron is
not confined or reflected by a magnetic or electrostatic field it leaves, going outwards to
surrounding space or hits the screen or vessel wall (or blanker) immediately after reaction. In
last instance, the neutron kinetic energy is converted to heat. The heat is taken away from the
screen by direct radiation or and indirect circulating coolant and can be used to run an electric
generator. If we add 6
Li inside the blanket, then tritium can be produced by reaction
n + 6
Li 4He (2.1 MeV) + T (2.7 MeV) (22)
and then used as the fuel. Another reaction product is the alpha particles 4He carrying 3.5
MeV which can be directed or confined by electro-magnetic field.
The reaction that produces only charged particles are best for the proposed propulsion
system and generator. Unfortunately, these reactions are not great (see Table 1).
However, since the nuclei are positively charged, they must have enough energy to
overcome the Coulomb repulsion between them, in order for a few of them to be able to
combine. The required energy can be estimated by equation (1).
2. Rocket Impulse. When we know the energy of the thermonuclear particles, the particle
speed can be calculated by equation
4 0.5
1.384 10 ( / ) Vi
E Ni
,
(23)
152 Alexander Bolonkin
where E is particle energy in MeV, N is number of nucleons in particle (in mass units, for
example, N = 1 for proton, neutron, N = 2 for deuterium, N = 3 for tritium, N = 4 for helium).
Conventionally, we have two components on the equation‘s right-side having different
mass and speed. The average efficiency particle speed V (impulse) of thermonuclear reaction
may be estimated by equation
2
2
1 2
1
1 V
N
N
V
N
N
V
(24)
where lower index "i" is number of particle, is coefficient utilization of kinetic particle
energy, N is total number of nucleons in single reaction. For particles adsorbed by screen
(Figure 1a) = 0.25, for particles reflected by reflector (Figure 1b) = 1.
When we use the radiation (photon) energy of one hot side of screen, the efficiency
particle speed (24) has additional member
m cN
E
V
p
J 3
(25)
where mp =1.6749510-27 kg is mass of neutron, c = 3108 m/s is the light speed,
EJ=1.610-19E energy of particle in J, 3 = 0.25 is coefficient utilization of heat energy.
The apparatus speed is
0
ln
M
M
V V
f
m
,
(26)
where Vm is maximum speed of space apparatus, m/s; Mf /M0 is ratio of a final mass
(apparatus without thermonuclear fuel) to the initial apparatus mass.
Results of computation are presented in Table #1.
Table 1.
Type of propulsion
Thermonuclear
reaction, MeV
AB-screen,
Impulse from
charged
particles
106 m/s
AB-screen.
Max speed of
apparatus for
Mf /M0 = 0.1
Speed106m/s
ABreflector.
Impulse
from
charged
particles
106 m/s
AB-reflector.
Max speed of
apparatus for
Mf /M0 = 0.1
Speed106m/s
Mass
ratio
Mf /M0
for
fuel=0
+
Photon.
Add
speed
106m/s
1 2 3 4 5 6 7
D+T4He(3.5)+
n(14.1)
5.18 8.13 10.3 23.8 0.19 0.23
T+T4He(3.77)+
2n(7.53)
4.48 7.03 8.96 20.6 0.25 0.15
D+3He4He(3.6)+
p(14.7)
5.28 8.29 21.1 48.5 0.1 -
New Concepts, Ideas and Innovations in Aerospace… 153
Type of propulsion
Thermonuclear
reaction, MeV
AB-screen,
Impulse from
charged
particles
106 m/s
AB-screen.
Max speed of
apparatus for
Mf /M0 = 0.1
Speed106m/s
ABreflector.
Impulse
from
charged
particles
106 m/s
AB-reflector.
Max speed of
apparatus for
Mf /M0 = 0.1
Speed106m/s
Mass
ratio
Mf /M0
for
fuel=0
+
Photon.
Add
speed
106m/s
1 2 3 4 5 6 7
D+6
Li2
4He(22.4) 5.8 9.11 23.6 54.3 0.1 -
3He+3He4He(4.3)+
2p(8.6)
5 7.85 20 46 0.1 -
3He+6
Li2
4He(1.9)+
p(16.9)
3 4.47 12 27.6 0.1 -
p+11B3
4He(8.7) 2.95 4.63 11.78 27.1 0.1 -
Here are: D - deuterium, T - tritium, He - helium, Li - lithium, B - boron, n - neutron, p - proton.
The first column shows the thermonuclear reaction. In left side from pointer it is shown
the components of thermonuclear reactor fuel. In the right-side it is shown the particles which
appear in the reaction and kinetic energy every particle in MeV.
The second column shows the efficiency impulse (in m/s) computed by equation (18) for
AB-screen engine.
The third column shows the maximum speed which apparatus (equipped with an engine
screen) reaches a fuel mass ratio equal to 0.1 (equation (20)).
The fourth and fifth column shows the efficiency impulse and maximum apparatus speed
for AB-reflector engine.
The sixth column shows the final mass of the space apparatus when the mass of initial
fuel equals zero. In the first two reactions this ratio is not 0.1 because the neutrons are
adsorbed by the screen. That decreases the apparatus speed, but the neutrons can be harnessed
to get additional fuel and to sustain other useful and valuable thermonuclear reaction. All
computation in Table 1 is made for mass ratio 0.1.
The last (seventh) column shows the additional speed from hot one-sided screen emitting
photons. This additional speed is small.
The thrust of the spherical thruster-generator (Figure1d) for small angles may be
computed as for AB-screen engine. Thrust is proportion the ratio of the open area to the full
sphere surface.
The power of electric generator may be estimated by equation
m E
N
N
W f
p
14
0.510
(27)
where W is power, W; Np is number of the charges (protons) nucleons; N is total number of
nucleons; E is energy of charged particles, MeV; mf
is fuel consumption, kg/s. is coefficient
efficiency.
The trust propulsion is
T mfV , (28)
154 Alexander Bolonkin
where T is trust, N.
The relative mass of fuel converted to energy and thrust is
N
E
m
938
(29)
where E is reaction energy in MeV.
For example, let us take the reaction D+T and fuel consumption mf = 10-5
kg/s. Then Np
/N = 4/5, E = 3.5 MeV and W 1.34106
kW; thrust T 100 N; the relative mass converted
into energy is 3.7510-3
. If the fuel consumption is mf = 10-2
kg/s, the thrust is T 105 N. The
energy is gigantic W 1.34109
kW.
Table 1 shows that the offered thermonuclear AB-propulsions can accelerate the space
apparatus up the speed (20 50)106 m/s (or up 1/6 of light speed) with a fuel ratio of Mf /M0
= 0.1. The AB-propulsion is the most efficient of all thermonuclear propulsions, capable of
reaching the theoretic maximum impulse from currently known thermonuclear propulsions
and known thermonuclear reactions.
Please note that the reaction that produces only charged particles is more efficient than
reactions producing neutrons and charged particles (two in the first lines of Table 1). The
neutrons accept a lot of a common energy, but this energy does not produce any thrust.
Converting this energy into photons (column 7 of table 1) is also ineffective. The neutrons do
not leave the space apparatus, increasing its final launch and travel weight (column 6) and
decreasing the final apparatus speed. They may be used for next reaction (see (22) and
below), but technical realization of such reaction is decidedly complex and presently
unproductive. See some of these reactions below. Unfortunately, most neutron reactions are
exoteric.
3. The thermonuclear reactions used the slow neutrons:
Table 2
Reaction Energy,
MeV
Cross section,
burns
3He + n 3H+p +0.764 5400
6Li + n 3H+ +4.785 945
7Be + n 7Li+p +1.65 51000
10B + n 7Li+ +2.791 3837
14N + n 14C+p +0.626 1.75
17O + n 14C+ +1.72 0.5
33S + n 33P+p +0.75 0.002
35Cl +n 35H+p +0.62 0.3
The spherical AB-engine can produce much electrical energy, but conversion of this
energy into vehicular thrust by common electric (ion) propulsion is inefficient in comparison
with the offered AB-engine.
New Concepts, Ideas and Innovations in Aerospace… 155
DISCUSSION
The potential space traveling apparatus speed 1/6 of light speed is maximum velocity
predicted by thermonuclear AB-propulsion. That speed allows Mars to be a destination in
minutes (or some days when apparatus has limited acceleration); that very high speed allows
short period trips throughout our Solar system. However, it is not sufficient for easy
interstellar space trips. The nearest star system is located at a distance of 3 - 5 light-years.
That means the trip requires a minimum of 40 - 60 years. But required fuel ratio Mf /M0 is
very high: acceleration and braking of moving apparatus needs 4-stage rocket having the ratio
for every stage Mf /M0 = 0.1. The total weight fuel ratio will be Mf /M0 = 10-4
. If useful weight
is 10 tonnes, the starting rocket mass is M0 /Mf = 104
tonnes. The relative mass of
thermonuclear reaction converted into energy (and thrust) is only 0.3 0.4% of total fuel
mass. The author‘s research so far shows that the magnet cannot adsorb the big amount of
interstellar matter in the high apparatus speed mode; consequently, the envisioned apparatus
must take fuel for the entire trip.
Human interstellar flight is very expensive and complex. We can develop long-distance
communication system and send, instead, E-men [18, 19] or artificial intelligent robot.
However, only an annihilation reaction can efficiently solve the interstellar trip macroproblem.
Otherwise, new physics discoveries that allow such trips is required.
Conclusion
The author suggests the simplest maximally efficient thermonuclear AB-propulsion (and
electric generators) based in the early offered size-minimized Micro-AB-thermonuclear
reactor [15]. These engines directly convert high-speed charged particles produced in
thermonuclear reactor into vehicular thrust or onboard vehicle electricity resource. Offered
propulsion system allows travel to any of our Solar System‘s planets in a short time as well as
trips to the nearest stars by E-being or intellectual robot in during a single human life [16 ]-
[17].
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: "Bolonkin", and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Bolonkin A.A., Beam Space Propulsion, Presented as paper AIAA-2006-7492 to
Conference "Space-2006", 19-21 September, 2006, San-Jose, CA, USA. Published in
http://Arxiv.org , Search: Bolonkin.
[2] Bolonkin A.A., Electrostatic AB-Ramjet Space Propulsion, Presented as paper AIAA2006-6173
to AIAA/AAS Astrodynamics Specialist Conference, 21-24 August 2006,
USA. Published in http://Arxiv.org . Search: Bolonkin.
156 Alexander Bolonkin
[3] Bolonkin A.A., Theory of Space Magnetic Sail Some Common Mistakes and
Electrostatic MagSail, Presented as paper AIAA-2006-8148 to 14th AIAA/AHI Space
Planes and Hypersonic Systems and Technologies Conference, 6 - 9 Nov 2006 National
Convention Centre, Canberra, Australia. Published in http://Arxiv.org .
[4] Bolonkin A.A., High Speed AB-Solar Sail, This work is presented as paper AIAA2006-4806
for 42 Joint Propulsion Conference, Sacramento, USA, 9-12 July, 2006.
Published in http://Arxiv.org .
[5] Bolonkin A.A., Electrostatic Utilization of Asteroids as Propulsion System. Presented
as paper AIAA-2005-4032 at the 41 Propulsion Conference, 10–12 July 2005, Tucson,
Arizona, USA.
[6] Bolonkin A.A., Electrostatic Solar Sail. Book "Non-Rocket Space Launch and Flight",
Elsevier, 2006, Ch.18, pp. 317-326.
[7] Bolonkin A.A., Electronic Solar Sail. Book "Non-Rocket Space Launch and Flight",
Elsevier, 2006, Ch.19, pp. 334-335.
[8] Bolonkin A.A., Multi-reflex Propulsion System for Space and Air Vehicles and Energy
Transfer for Long Distance. Book "Non-Rocket Space Launch and Flight", Elsevier,
2006, Ch.12, pp. 223-244. See also: JBIS, 2004, vol.57, No. 11/12, pp.379-390.
[9] Bolonkin A.A., Electrostatic Solar Wind Propulsion. Presented as paper AIAA-2005-
3857 at the 41st Propulsion Conference, 10-12 July 2005, Tucson, AZ, USA. See also
book "Non-Rocket Space Launch and Flight", Elsevier, 2006, Ch.13, pp. 245-270.
[10] Bolonkin A.A., Electrostatic Utilization of asteroids for space flight. Presented as paper
AIAA-2005-4032 at the 41st Propulsion Conference, 10-12 July 2005, Tucson, AZ,
USA. See also book "Non-Rocket Space Launch and Flight", Elsevier, 2006, Ch.14, pp.
271-280.
[11] Bolonkin A.A., Guided solar sail and energy generator. Presented as paper AIAA-2005-
3857 at the 41st Propulsion Conference, 10-12 July 2005, Tucson, AZ, USA. See also
book "Non-Rocket Space Launch and Flight", Elsevier, 2006, Ch.15, pp. 302-308.
[12] Bolonkin A.A., Radioisotope Space Sail and Electr0-Generator. Presented as paper
AIAA-2005-4225 at the 41st Propulsion Conference, 10-12 July 2005, Tucson, AZ,
USA. See also book "Non-Rocket Space Launch and Flight", Elsevier, 2006, Ch.17, pp.
309-316.
[13] Bolonkin A.A., Wireless Transfer of Electricity in Outer Space. Presented as paper
AIAA-2007-0590 to 45th AIAA Aerospace Science Meeting, 8 - 11 January 2007,
Reno, Nevada, USA. Published in http://Arxiv.org .
[14] Bolonkin A.A., Non-Rocket Space Launch and flight, Elsevier, 2006,
http://Bolonkin.narod.ru/p65.htm.
[15] Bolonkin A.A., Micro-Thermonuclear AB-Reactors for Aerospace. Presented as paper
AIAA-2006-8104 in 14th Space Plane and Hypersonic Systems Conference, 6-8
November, 2006, USA; Published in http://arxiv.org .
[16] Bolonkin A.A., Breakthrough to Immortality, 2004, http://Bolonkin.narod.ru .
[17] Bolonkin A.A., Humanity and Space Civilization, 2000,
http://Bolonkin.narod.ru/p101.htm .
[18] Nishikawa K., Wakatani M., Plasma Physics, Spring, 2000.
[19] Handbook of Physical Quantities, Ed. Igor S. Grigoriev, 1997, CRC Press, USA.
New Concepts, Ideas and Innovations in Aerospace…
Attachment to Part A, Ch. 7. Possible thermonuclear propulsion
158 Alexander Bolonkin
Chapter 8
A NEW METHOD OF ATMOSPHERIC REENTRY
FOR SPACE SHIPS
ABSTRACT
In recent years, industry has produced high-temperature fiber and whiskers. The
author examined the atmospheric reentry of the USA Space Shuttles and proposed the use
of high temperature tolerant parachute for atmospheric air braking. Though it is not large,
a light parachute decreases Shuttle speed from 8 km/s to 1 km/s and Shuttle heat flow by
3 - 4 times. The parachute surface is opened with backside so that it can emit the heat
radiation efficiently to Earth-atmosphere. The temperature of parachute is about
1000-1300o C. The carbon fiber is able to keep its functionality up to a temperature of
1500-2000o C. There is no conceivable problem to manufacture the parachute from
carbon fiber. The proposed new method of braking may be applied to the old Space
Shuttles as well as to newer spacecraft designs.
Keywords: Atmospheric reentry, Space Shuttle, thermal protection of space apparatus,
parachute braking.
INTRODUCTION
In 1969 author applied a new method of global optimization to the problem of
atmospheric reentry of spaceships [1 p. 188]. The general analysis presented an additional
method to the well-known method of outer space to Earth-atmosphere reentry ("high-speed
corridor"). There is a low-speed corridor when the total heat is less than in a conventional
high-speed passage. In that time for significantly decreasing the speed of a spaceship retroand
landing rocket engine needed to be used. That requires a lot of fuel. It is not acceptable
for modern spaceships. Nowadays the textile industry produces heat resistant fiber that can be
used for a new parachute system to be used in a high-temperature environment [2]-[4].
Presented as Bolonkin‘s paper AIAA-2006-6985 to Multidisciplinary Analysis and Optimization Conference, 6-8
Sept. 2006, Portsmouth, Virginia. USA
New Concepts, Ideas and Innovations in Aerospace… 159
Figure 1. Space Shuttle "Atlantic". during
reentry.
Figure 2. The outside of the Shuttle heats to over
1,550 °C
Figure 3. Endeavour deploys drag chute after touch-down.
THEORY
Equations of spaceship reentry are:
2 cos ,
cos
cos
sin ,
sin ,
cos ,
0
E E
P
P
R
V
V
g
mV
L L
g
m
D D
V
H V
V
R
R
r
(1)
160 Alexander Bolonkin
where r is range of ship flight, m; R0 = 6,378,000 is radius of Earth, m; R is radius of ship
flight from Earth's center, m; V is ship speed, m/s; H is ship altitude, m; is trajectory angle,
radians; D is ship drag, N; DP is parachute drag, N; m is ship mass, kg; g is gravity at altitude
H, m/s2
; L is ship lift force, N; LP is parachute lift force, N; E is angle Earth speed; E = 0 is
lesser angle between perpendicular to flight plate and Earth polar axis; t is flight time, sec.
The magnitudes in equations (1) compute as:
0.5 , / 3, 2 , / 4,
, 273,
100
100
, ,
0.5 11040 10
, , 0.414, 6719,
1
1/ 4
4
2
1
0.5 3.1 5
0.5
4
1
( 10000)/
1
2
0
0
0
D C aVS L D L aVS D L
T T
T
C
Q
T
S
R
V
V
R
Q
a e a b
R H
R
g g
P DP P P P
S
P
n
n S L CO
H b
(2)
where: g0 = 9.81 m/s2
is gravity at Earth surface; is air density, kg/m3
; Q is heat flow in 1
m
2
/s of parachute, J/s.m
2
; Rn (or Rp) is parachute radius, m; SP (or Sm) is parachute area, m2
;
SL= 1.225 kg/m3
is air density at sea level; VCO = 7950 m/s is circle orbit speed; T1 is
temperature of parachute in stagnation point in Kelvin,
oK; T is temperature of parachute in
stagnation point in centigrade, oC; T2 is temperature of the standard atmosphere at given
altitude, oK; DP is parachute drag, N; LP is parachute lift force, N (the ram-air parachute can
produce lift force up 1/3 from its drag); D is ship drag, N; L is ship lift force, N; CDP = 1 is
parachute drag coefficient; a = 295 m/s is sound speed; = 40o
= 0.7 rad is ship attack angle.
Figure 4. Space Shuttle Thermal Protection System Constituent Materials.
New Concepts, Ideas and Innovations in Aerospace… 161
The control is following: if d/dt > 0 the all lift force L = LP = 0. When the Shuttle riches
the low speed the parachute area can be decreased or parachute can be detached. That case
not computed. Used control is not optimal.
The results of integration are presented below. Used data: parachute area are SP = 1000,
2000, 4000 m2
(Rp = 17.8, 25.2, 35.7 m); m = 104,000 kg. The dash line is data of the Space
Shuttle without a parachute.
Figure 5. Decreasing of Space Shuttle speed with parachute and without it. Sm = SP.
Figure 6. Space Shuttle trajectory with parachute.
162 Alexander Bolonkin
Figure 7. Temperature of parachute at stagnation point.
Figure 8. Heat flow through 1 m2
/s of Space Shuttle surface at stagnation point with parachute and
without it.
New Concepts, Ideas and Innovations in Aerospace… 163
DISCUSSION OF RESULTS
Figure 5 shows the parachute significantly decreases the shuttle speed from 8000 m/s to
350 - 2900 m/s after 550 sec of reentry flight. Practically, the Space Shuttle overpasses the
heat barrier (maximum of heat flow) near 200 sec into its reentry (see Figure 8). The heat
flow depends on the power 3.15 from speed (see the second equation in (2)) and the speed
strongly influences the heat flow. For example, the decreasing of speed in two times
decreases the heat flows in 8.9 times!
Figure 6 shows: at altitude 41 - 44 km the ship has speed 350 - 2900 m/s which is
acceptable for high speed vehicle in short time of reentry.
Figure 7 shows the maximum temperature in a stagnation point of the parachute. It is
1000 - 1300o C. The parachute can be made from carbon fiber that can keep the temperature
1500 - 2000o C (carbon melting temperature is over 3000o C). At present a carbon fiber
composite matters uses by Shuttle for leader edges of Shuttle where temperature reaches
1550o C.
Figure 8 gives the heat flow through 1 m2
/s of Shuttle without or with a parachute. If we
continue flight time up 750 sec, the special total heat will be following: without parachute it is
11.84108
J/m2
, for parachute having area 1000 m2
- 7108
J/m2
, for 2000 m2
parachute -
5108
J/m2
, for 4000 m2
parachute - 3.5108
J/m2
. That is about 1.7 - 3.4 times less then
without parachute. It means the future Space Shuttles can have a different system of heat
protection and a modern design can be made lighter and cheaper.
ESTIMATION PARACHUTE SYSTEM
The weight of the parachute system and a comparison with current heat protection is key
moment for this innovative method. Industry has produced many metal and mineral fibers and
whiskers having very high tensile stress at high temperatures. Let us to estimate the mass of
parachute system. Assume the carbon fiber having the maximum tensile stress = 565
kg/mm2
( = 5.65109 N/m2
) at temperature T = 1500 - 2000o C is used for parachute. Let us
take the safety margin 2.3 - 3. That means = 150 kg/mm2
for canopy and = 200 kg/mm2
for cord. The fiber density is taken = 3000 kg/m3
.
The computation is presented in Table 1.
Currently, the mass of the heat protection in Shuttle is 9575 kg. If we decrease this
protection proportional the decreasing of the heat flow (in 2 - 3 times) we save the 4 - 6 tons
of Shuttle mass.
At the present time, the changing of hundreds of hull protection tiles after every flight
takes two weeks and very costly to do. The new method requires only a few tile replacements
(maximum temperature is less) or allows using a protective cooling method.
The Command Module of spacecraft "Apollo" had a heat protection of approximately 1/3
of the total take-off/touchdown weight. The gain to be had from a new method reentering may
be significantly more.
164 Alexander Bolonkin
Table 1. Parachute data
Parachute area Sp= Sm, m2
1000 2000 4000
Reference parachute radius Rp, m 17.8 25.2 35.7
Max. parachute pressure Pp, N/m2
1250 2000 6000
Parachute surface Spc= 2Rp
2 m
2 2000 4000 8000
Parachute thickness =PpRp/2, mm 0.0074 0.0076 0.0072
Mass of canopy Mc=Spc, kg 45 90 171
Mass of cord, kg 66 132 258
Total mass, kg 111 226 429
Max. brake force, kN 1250 1800 2400
Add. Max. overload, g 1.25 1.8 2.4
CONCLUSION
The widespread production of high temperature fibers and whiskers allows us to design
high-temperature tolerant parachutes, which may be used by space apparatus of all types for
braking in a rarified planet atmosphere. The parachute has open backside surface that rapidly
emits the heat radiation to outer space thereby quickly decreasing the parachute temperature.
The proposed new method significantly decreases the maximum temperature and heat flow to
main space apparatus. That decreases the heat protection mass and increases the useful load
of the spacecraft. The method may be also used during an emergency reentering when
spaceship heat protection is damaged (as in horrific instance of the Space Shuttle
"Columbia").
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: Bolonkin, and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Bolonkin A.A., New Methods of Optimization and their Application, Moscow High
Technical University named Bauman, 1972, 220 ps, (in Russian).
[2] .Bolonkin A.A., Non-Rocket Space Launch and Flight, Elsevier, 2006, 488 ps.
[3] Bolonkin, A.A. Electrostatic AB-Ramjet Space Propulsion, AIAA-2006-6173.
http://arxiv.org.
[4] Regan F.J., Anandakrishnan S.M., Dynamics of Atmospheric Re-Entry, AIAA, 1993.
New Concepts, Ideas and Innovations in Aerospace…
Chapter 9
OPTIMAL SOLID SPACE TOWER
ABSTRACT
Theory and computations are provided for building of optimal (minimum weight)
solid space towers (mast) up to one hundred kilometers in height. These towers can be
used for tourism; scientific observation of space, observation of the Earth‘s surface,
weather and upper atmosphere experiment, and for radio, television, and communication
transmissions. These towers can also be used to launch spaceships and Earth satellites.
These macroprojects are not expensive. They require strong hard material (steel).
Towers can be built using present technology. Towers can be used (for tourism,
communication, etc.) during the construction process and provide self-financing for
further construction. The tower design does not require human work at high altitudes; the
tower is separated into sections; all construction can be done at the Earth‘s surface.
The transport system for a tower consists of a small engine (used only for friction
compensation) located at the Earth‘s surface.
Problems involving security, control, repair, and stability of the proposed towers are
addressed in other cited publications.
Keywords: Space tower, optimal space mast, space tourism, space communication,
space launch, space observation.
1.INTRODUCTION
1.1. Brief History
The idea of building a tower high above the Earth into the heavens is very old [1]. The
writings of Moses, in chapter 11 of his book Genesis refers to an early civilization that tried to
build a tower to heaven out of brick and tar. This construction was called the Tower of Babel,
and was reported to be located in Babylon in ancient Mesopotamia. Later in chapter 28, Jacob
had a dream about a staircase or ladder built to heaven. This construction was called Jacob‘s
Ladder. More contemporary writings on the subject date back to K.E. Tsiolkovski in his
Presented as Bolonkin‘s paper AIAA-2007-0367 to 45th AIAA Aerospace Science Meeting, 8 - 11 January 2007,
Reno, Nevada, USA. (see details in author's works: AIAA-2006-4235, AIAA-2006-7717).
166 Alexander Bolonkin
manuscript ―Speculation about Earth and Sky and on Vesta,‖ published in 1895 [2]. This idea
inspired Sir Arthur Clarke to write his novel, The Fountains of Paradise [3], about a space
tower (elevator) located on a fictionalized Sri Lanka, which brought the concept to the
attention of the entire 20th Century world.
Today, the world‘s tallest construction is a television transmitting tower (mast) near
Fargo, North Dakota, USA. It stands 629 m high and was built in 1963 for KTHI-TV. The
CNN Tower in Toronto, Ontario, Canada is the world‘s tallest building. It is 553 m in height,
was completed in1975, and has the world‘s highest observation deck at 447 m. The tower
structure is concrete up to the observation deck level. Above is a steel structure supporting
radio, television, and communication antennas. The total weight of the tower is 3,000,000
metric tons.
The Ostankin Tower in Moscow is 540 m in height and has an observation desk at 370 m.
The world‘s tallest office building is the Petronas Towers in Kuala Lumpur, Malasia. The
twin towers are 452 m in height. They are 10 m taller than the Sears Tower in Chicago,
Illinois, USA. The Skyscrapers (Taipei, Taiwan, 2004) has height of 509 m, the Eiffel Tower
(Paris, 1887-1889) has 300 m, Empire State Building (USA, New York, 1930-1931) has 381
m + TV mast of 61 m. Under construction a building of 1001 m (Kuwait City, Kuwait) and
1430 m Supported Structure in Gulf of Mexico.
Current materials make it possible even today to construct towers many kilometers in
height. However, conventional towers are very expensive, costing billions of dollars. When
considering how high a tower can be built, it is important to remember that it can be built to
any height if the base is large enough. Theoretically, you could build a tower to
geosynchronous Earth orbit (GEO) out of bubble gum, but the base would likely cover half
the surface of the Earth.
The proposed optimal masts (towers) are cheaper in lots of hundreds. They can be built
on the Earth‘s surface and their height can be increased as necessary. Their base is not large.
The main innovations in this project are the application of optimal structures (minimum
weight), hydrogen for filling tube structures at high altitude and a solution of a stability
problem for tall (thin) solid columns, and utilization of new materials [4]-[7].
The tower applications. The high towers (3-100 km) have numerous applications for
government and commercial purposes:
• Entertainment and Observation platform.
• Entertainment and Observation desk for tourists. Tourists could see over a huge area,
including the darkness of space and the curvature of the Earth‘s horizon.
• Drop tower: tourists could experience several minutes of free-fall time. The drop
tower could provide a facility for experiments.
• A permanent observatory on a tall tower would be competitive with airborne and
orbital platforms for Earth and space observations.
• Communication boost: A tower tens of kilometers in height near metropolitan areas
could provide much higher signal strength than orbital satellites.
• Solar power receivers: Receivers located on tall towers for future space solar power
systems would permit use of higher frequency, wireless, power transmission systems
(e.g. lasers).
New Concepts, Ideas and Innovations in Aerospace… 167
• Low Earth Orbit (LEO) communication satellite replacement: Approximately six to
ten 100-km-tall towers could provide the coverage of a LEO satellite constellation
with higher power, permanence, and easy upgrade capabilities.
• Other new revolutionary methods of access to space are described in [8]-[15].
2. DESCRIPTION OF INNOVATION AND PROBLEM
2.1. Tower Structure
The simplest tourist tower includes (Figure 1): Solid mast, top observation desk, elevator,
expansions, and control stability. The tower is separated into sections by horizontal and
vertical rods (Figure2) and contains control devices.
Figure 1. Solid optimal space tower (mast) of height 3 - 100 km. (a) typical cross-section of tower.
Notations: 1 – solid column; 2 – observation desk; 3 – load cable elevators; 4 – passenger cabin; 5 –
expansions; 6 – engine; 7 – radio and TV antenna; 8 – rollers of cable transport system; 9 – stability
control.
2.2. Filling Gas
The compressed gas should fill the tube tower rods that provide the structure's weight.
Author suggests filling the towers with a light gas, for example, hydrogen.
The average temperature of the atmosphere in the interval from 0 to 100 km is about
240oK.
2.3. The Observation Radius
Versus altitude is presented in [8], figures 4-5 [Eq. (23)].
168 Alexander Bolonkin
Figure 2. Section of optimal solid tower. Notation: (a) - the first level tube rod with sold diagonal
braces; (b) - the first level rod with flexible braces; (c) - the second level rod with lattice column and
braces; (d) - cross-section of rods.
2.4. Tower Material
The tower parameters very depend on the strength of material, specifically the relation of
the safety press stress to specific density . Pressure limit is approximately three times more
then tensile stress for most conventional materials.
The properties of the some current materials are presented in Table 1.
Current industry widely produces artificial fibers having tensile stress = 500 - 620
kg/mm2
and density = 1800 kg/m3
. Their tensile ratio is K =10 -7
/ = 0.28 - 0.34. There
are whisker (in industry) and nanotubes (in scientific laboratory) having tensile K = 1 - 2
(whisker) and K = 5 - 11 (nanotubes). Theory predicts fiber, whisker and nanotubes having K
ten times greater [5]-[7]. These materials can be used for light guy-lines.
Table 1. Compressive strength of some materials (Kikoin [4], ps. 38, 41, 52, 54)
Material Density
[kg/m3
]
Pressure limit
10 -7
[N/m2
]
Strength coefficient
K=10 -7
/
Tensile stress
10 -7
[N/m2
]
Steel, 40X 7900 400 0.050 120
Alloy WC 19000 600 0.032 110
Duralumin 2900 150 0.052 54
Quartz 2650 1200 0.453 -
Corundum 4000 2100 0.525 -
Diamond 3520 9859 2.8 -
New Concepts, Ideas and Innovations in Aerospace… 169
The tower parameters have been computed for pressure K = 0.05 - 0.3. Recommend value
for guy- lines is K = 0.1.
2.5. Tower Safety
For safety of people (passenger cabin) parachutes can be used.
2.6. Tower Stability
Stability is provided by expansions (tensile elements). The verticality of the tower (mast)
can be checked by laser beam and GPS sensors monitoring beam location (Figure2). If a
section deviates from vertical control cables, control devices automatically restore the tower
position.
2.7. Tower Construction
The tower building will not have conventional construction problems such as lifting
building material to high altitude. The tower (mast) is not heavy. New sections are put under
the tower, the new section is lifted, and the entire tower is lifted. It is estimated the building
may be constructed in 4 -12 months. A small tower (up to 3 km) can be located in city.
2.8. Tower Cost
The tower does not require high-cost building materials. The tower will be a tens times
cheaper than conventional reinforced concrete towers 400 - 600 m tall.
3. THEORY OF OPTIMAL SOLID TOWER
Equations developed and used by author for estimations and computation are provided
below.
1. Optimal Cross-Section Area for Solid Tower of Compressive Stress
Optimal cross-section area for space elevator cable (tensile stress) the author received in [9],
Eqs. (1) - (5), (see also [10], Ch.1). For compressive stress we must change the sign (" -") at
value B. The equation (4) for our case (rotary Earth and variable gravity) is
( ) , , 10 ,
( )
1
2
1 1
, ( )
( )
( ) exp
0 7
2
0 0
2
0
2
0
0
0
0
A r dr k K k
kA R
g
G
M M
R
R
R R g
B R R
g B R
A
A
A R
R
R
(1)
where A is cross-section area of solid tower, m2
; A0 is initial (at ground) cross-section area,
m
2
;
A
is relative cross-section area of tower (mast); R is radius (distance from Earth center),
m; R0 is Earth radius, m, R0 = 6.378 km; g0 = 9.81 m/s2 is Earth gravity at Earth surface; =
170 Alexander Bolonkin
72.68510 -6
rad/s is Earth angle speed, G is vertical force at tower top, kg; M is tower
weight, kg;
M
is relative tower weight (weight for every unit load mass).
If the gravity is constant and Earth does not rotate, the equation (1) is simpler
exp exp , where , 1
0 0 k
g h
e
G
M k M
k
g H g H
A
(2)
The computations for tower height H = 100 km and for tower H = 37,000 km
(geosynchronous orbit) are presented in Figure 3 - 7.
Figure 3. Relative tower cross-section aria versus tower altitude (up 100 km) and pressure strong
coefficient.
Figure 4. Relative tower mass for height H = 100 km versus pressure stress coefficient K.
New Concepts, Ideas and Innovations in Aerospace… 171
Figure 5. Relative cross-section ratio S/S0 for the tower height H = 37,000 km (geosynchronous orbit)
versus the pressure stress coefficient K.
Figure 6. Relative tower mass for tower height H = 37,000 km (geosynchronous orbit) versus pressure
stress coefficient K = 0.2 - 0.4.
172 Alexander Bolonkin
Figure 7. Relative tower mass for tower height H = 37,000 km (geosynchronous orbit) versus pressure
stress coefficient K = 0.2 - 1.
The figures 3 - 4 show the optimal steel tower (mast) having the height 100 km, safety
pressure stress K = 0.02 (158 kg/mm2
) must have the bottom cross-section area approximately
in 100 times more then top cross-section area and weight is 135 times more then top load
(Figure 4). For example, if full top load equals 100 tons (30 tons support extension cable + 70
tons useful load), the total weight of main columns 100 km tower-mast (without extension
cable) will be 13,500 tons . It is less that a weight of current sky-scrapers (compare with
3,000,000 tons of Toronto tower having the 553 m height). In reality if the safety stress
coefficient K = 0.015, the relative cross-section area and weight will sometimes be more but it
is a possibility of current building technology.
The figures 5 - 7 show the building of the geosynchronous tower-mast (include the
optimal tower-mast) is very difficult. For K = 0.3 (it is over the top limit margin of safety for
quartz, corundum) the tower mass is ten millions of times more than load (Figure 6), the
extensions must be made from nanotubes and they weakly help. The problems of stability and
flexibility then appear. The situation is strongly improved if tower-mast built from diamonds
(relative tower mass decreases up 100, Figure 7). But it is not known when we will receive
the cheap artificial diamond in unlimited amount and can create from it building units.
2. Using the Compressive Rods [9]
The rod compressed by gas can keep more compressive force because internal gas makes
a tensile stress in a rod material. That longitudinal stress cannot be more then a half safety
tensile stress of road material because the compressed gas creates also a tensile radial rod
force (stress) which is two times more than longitudinal tensile stress. As the result the rod
material has a complex stress (compression in a longitudinal direction and a tensile in the
radial direction). Assume these stress is independent. The gas has a weight which must be
New Concepts, Ideas and Innovations in Aerospace… 173
added to total steel weight. The author used the following equations for computation of the
gas compressive rods
Figure 8. Current high tower.
Figure 9. Current and project high towers.
RT
K p
RT
r p
g
g
g
t
g
c t g
,
,
2 2
,
2
1
0 0
(3
)
where g is safety stress of gas compressed rod, N/m2
; c
is safety load compressed stress,
N/m2
; t
is safety tensile gas stress, N/m2
; g is specific density of gas compressed rod, kg/m3
;
174 Alexander Bolonkin
o is specific density conventional rod, kg/m3
; is the gas molar weight (for hydrogen H2 it
equals = 0.002 kg/mole), R = 8.314 is constant, T is temperature), oK; p is gas pressure,
N/m2
; is gas density, kg/m3
; is wall thickness of rod, m; r is rod radius, m.
For steel and duralumin from Table 1, the internal gas increases K in 35 - 45%.
Unfortunately, the gas support depends on temperature (see Eq. (3)). That means the mast
can loss this support at night. Moreover, the construction will contain the thousands of rods
and some of them may be not enough leakproof or lose the gas during of a design lifetime. I
think it is a danger to use the gas pressure rods in space tower.
CONCLUSION
The inexpensive steel tower-mast of the height up 100 - 200 km (and more) can be built
without big problems at the present time. They can be useful for communication (TV, radio,
telephone), for radiolocation (defense), for space launch, for tourism (include space tourism),
for scientists (astronomy), for solar energy, and for many other applications. The offered
optimal design allows finding of the minimum of a tower-mast weight which can be reached
in this space building.
The other designs of space towers are in [8]-[15].
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: Bolonkin, and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] D.V. Smitherman, Jr., Space Elevators, NASA/CP-2000-210429.
[2] K.E. Tsiolkovski: ‖Speculations about Earth and Sky on Vesta,‖ Moscow, Izd-vo AN
SSSR, 1959; Grezi o zemle I nebe (in Russian), Academy of Sciences, U.S.S.R.,
Moscow, p.35, 1999.
[3] A.C. Clarke: Fountains of Paradise, Harcourt Brace Jovanovich, New York, 1978.
[4] N.K. Kikoin (Ed.), Tables of Physic Values, Atom Publish House, Moscow, 1976, (in
Russian).
[5] F.S. Galasso, Advanced Fibers and Composite, Gordon and Branch Science Publisher,
1989.
[6] Carbon and High Perform Fibers, Directory, 1995.
[7] M.S. Dresselhous, Carbon Nanotubes, Springer, 2000.
[8] A.A. Bolonkin, Optimal Inflatable Space Tower with 3 - 100 km Height, JBIS, Vol. 56,
pp.87-97, 2003.
[9] A.A. Bolonkin, Non-Rocket Transport System for Space Travel, JBIS, Vol, 56, No.7/8,
pp.231 - 249, 2003.
[10] A.A. Bolonkin, Non-Rocket Space Launch and Flight, Elsevier, London, 2006, 488 pgs.
Chapters 4 - 5, pp.83 - 124.
[11] A.A. Bolonkin, Kinetic Space Towers, Presented as paper IAC-02-IAA.1.3.03 at World
Space Congress -2002. 10-19 October, Houston, TX, USA.
[12] A.A. Bolonkin, Kinetic Space Towers and Launchers, JBIS, Vol. 57, No. 1/2, pp.33-39,
2004.
New Concepts, Ideas and Innovations in Aerospace… 175
[13] A.A. Bolonkin, Optimal Space Towers. AIAA-2006-4235.
[14] A.A. Bolonkin, Solid Space Towers. AIAA-2006-7717. http://axiv.org , search:
"Bolonkin".
[15] A.A. Bolonkin, Space Towers, in book "Macro-Engineering: A Challenge for the
Future". Springer, 2006, pp. 121-150.
176 Alexander Bolonkin
Chapter 10
ELECTROSTATIC LINEAR ENGINE AND
CABLE SPACE AB LAUNCHER
ABSTRACT
This is suggested a revolutionary new electrostatic engine. This engine can be used
as a linear engine (accelerator), a strong space launcher, a high speed delivery system for
space elevator, Earth-Moon, Earth-Mars, electrostatic train, levitation, conventional high
voltage rotating engine, electrostatic electric generator, weapon, and so on. Author
developed theory of this engine application and shows powerful possibility in space,
transport and military industry. The projects are computed and show the good potential of
the offered new concepts.
Keywords: electrostatic linear engine, electrostatic accelerator, space launcher,
electrostatic train, electrostatic weapon.
INTRODUCTION
General. The aviation, space, and energy industries need revolutionary ideas which will
significantly improve the capability of future ground, air and space vehicles. The author has
offered a series of new ideas [1-59] contained in a) numerous patent applications [3 -18], b)
manuscripts that have been presented at the World Space Congress (WSC)-1992, 1994 [19
-22], the WSC-2002 ]23 -32], and numerous Propulsion Conferences [33 -39], and c) other
articles [40 -65].
In this Chapter a revolutionary method and implementations for future space flights and
ground systems are proposed. The method uses a highly charged surface. The proposed space
launch system creates tens of tons of thrust and accelerates space apparatus to high speeds.
History. In early works and patent applications (1965 - 1991), in World Space Congress2002
and other scientific forums the author suggested a series new cable launchers, space
This work is presented as Bolonkin‘s paper AIAA-2006-5229 for 42 Joint Propulsion Conference, Sacramento,
USA, 9-12 July, 2006. Work is published in Aircraft Engineering and Aerospace Technology: An International
Journal, Vol 78, #6, 2006, pp.502-508.
New Concepts, Ideas and Innovations in Aerospace… 177
transport systems, space elevator, anti-gravitator, kinetic space tower, and other systems,
which decrease the cost of space launch in thousands times or increase the possibilities
ground systems. All of them need in linear engine. In particular, there are: Cable Space
Launcher [23-25], Earth-Moon Transport system [29,39], Earth-Mars Transport System [30],
Circle Space Launcher [31], Air Cable aircraft [32, 41, 42], Non-Rocket Transport System for
Space Elevator (Elevator climber)[36], Centrifugal Keeper [38], Asteroid Propulsion System
[27, 40], Kinetic Space Towers [43], Long Transfer of Mechanical Energy [45], High Speed
Catapult Aviation [55], Kinetic Anti-gravitator [55], Electrostatic Levitation [59], and so on
(Figure 1).
The author offers electrostatic engines which can be used for every noted installation as
driver. That solved the second main problem of noted installation - how drive a vehicle along
a monorail by the electrostatic engine or the cable at high speed (some km/sec) to create a
powerful thrust.
DESCRIPTION OF ELECTROSTATIC LINEAR ENGINE
The linear electrostatic engine (space accelerator) for launching of space ship [23-25]
includes the following main parts (Figure 2): stator, thrust cable, charger of cable, high
voltage electric alternating current line. As additional devices the engine can have a gas
compaction, and vacuum pump.
The cable has a strong core (it keeps tensile stress - thrust) and dielectric cover contained
electric charges. The conducting layer is very thin and we neglect its weight. A detailed linear
engine (accelerator) for Cable Space Launcher is presented in Figure 3.
Figure 1. Installations needing the linear electrostatic engine. (a) Space cable launcher [23, 24, 35]; (b)
Circle launcher [31]; (c) Space keeper [38]; (d) Kinetic space tower [43]; (e) Earth round cable space
keeper [36]; (f) Cable aviation [32,41,42]; (g) Levitation train [59].
178 Alexander Bolonkin
Figure 2. Electrostatic engine (accelerator) for Space Cable Launcher [23 -25]. (a) Engine (side view);
(b) Engine (Forward view); (c) Running wave of voltage (charges) moves the charged cable; (d) - (f)
Different cross-section areas of engine: (d) - conventional; (e) - for moving aircraft or space ship; (f) -
for big thrust. Notations: 1 - stator of engine; 2 - thrust cable (rotor of engine); 3 - charges; 4 -
recharger; 5 - high voltage line; 6 - alternating current (voltage); 7 - gas compaction; 8 - vacuum pump.
Figure 3. Detail electrostatic engine (accelerator) for Space Cable Launcher. (a) Accelerator, (b)
Running voltage wave for stator, (c) Stationary charges into cable. Notation: 1 - stator; 2 - mobile rotor
(cable); 3 - charges; 4 - dielectric (isolator); 5 - running wave of voltage; 6 - curve of stationary cable
charges. U is voltage, C is charge. Lagging between voltage wave of stator (b) and charges of mobile
cable (c) is 90 degree.
New Concepts, Ideas and Innovations in Aerospace… 179
The engine works in the following mode. The cable has a set of stationary positive and
negative charges. These charges can be restored if they are relaxed. Outer generator creates a
running wave of voltage (charges) along stationary stator. This wave (charges) attracts the
opposed charges in rotor (cable) and moves (thrusts) it.
Bottom and top parts of cable (or stator) have small different charge values. This
difference creates a vertical electric field which supports the cable in suspended position
inside stator non-contact bearing and zero friction. The cable position inside stator is
controlled by electronic devices.
Charges have toroidal form (row of rings) and located inside a good dielectric having
high disruptive voltage. The stator toroids have conducting layer which allows changing the
charges with high frequency and produces a running high voltage wave. The offered engine
creates a large thrust (see computation below), reaches a very high (not limited) variable
speed of cable (km/s), to change the moving of cable in opposed direction, to fix a cable in
given position. The engine can also to work as high voltage electric generator when cable is
braking or moved by mechanical force. The space elevator climber (and many other mobile
apparatus) has constant charge, the cable (stator) has running charge. The weight of electric
wires is small because the voltage is very high.
THEORY OF OFFERED ELECTROSTATIC ENGINE
(ACCELERATOR)
1. Estimation of Thrust
Let us consider a single charged toroidal ring,1, in cable (Figure 3). The charge 1 attracts
to the opposed charges and repels from the same charges located into stator. Let us compute
the sum force acting to this single charge.
F QE Q l
r
E k
i
i
i
i
,
,
2
(1)
where E is electric intensity [V/m], k = 9109
is electric coefficient [N.m
2
/C2
], is linear
charge [C/m], is dielectric constant, ri
is distance between centers of charges [m], F is force
[N], Q is charge [C], l is length of linear charge [m].
If we take distance between charged rows of stator and cable d = 3a (Figure3), where a is
smaller radius of charged toroid, the ri are:
3 (4 2) , 13, 45, 109, 205, ... 1 2 3 4
2 2
ri
a i or r a r a r a r a
(2)
Substitute (2) in (1) we receive
k
a E
r
d
where
r
k
F
s
i
i
i i
i i
2
cos ,
cos ( 1)
4 1
2
(3)
180 Alexander Bolonkin
where Es
is safety dielectric strength [V/m], is angle between r and horizontal line
(Figure4).
Figure 4. Computation of thrust force of linear electrostatic engine for space ship accelerator. (a) Side
view stator and cable; (b) cross-section area. Notations: 1 - cable; 2 - stator; 3 - single charge in cable; 4
- electric charges in stator; 5 - toroidal form of electric charges into stator and cable; 6 - dielectric; a -
radius of charge (smaller radius of toroid); d - distance between layers of charges of stator and cable; r -
distance to charges.
Let us consider the row in (3)
... 0.05 , where 0.05
205
1
109
1
45
1
13
1
( 1)
cos ( 1)
2 2 2 2
1 1
b
a
d
b
a
d
a
d
r
d
r i
i
i
i
i
i
i (4)
This infinity row has sum and this sum equals b.
We computed force for one cable toroid. The cable has N toroid, N = L/4a, where L is
length of stator. After substitute (3), (4) in the first equation (3) the total force, FN, is
, where 0.04 0.05 for our case.
4
3
2
b
k
E Ll
F FN b
s
N
(5)
Estimate this force for area L l = 1 m2
, dielectric strength Es = 3106
- 3108 V/m, = d
= 1 - 3. Result is presented in figures 5 - 6.
In common case for plates the Equation (5) is
,
2
,
4
1
,
8
2
0
0
2 E S
k F b
k
E S
F b
(5a)
where F is force, N; S is charged area, m2
; b is coefficient of charged form and sign. For
opposed charges and plates that equals about 0.82 (F is compressing of a charged material),
for same F produces a tensile stress in the charged material, o = 8.8510-12 F/m.
As reader can see the force is very high and can reach up to 106 N/m2
=100 ton/m2
. That
means we can move big space ships and space probes. To get this thrust by conventional
electromagnetic launcher (as offered by other) gigantic and very expensive superconductive
magnets are needed. We made computation for d = 3a and distance between center of charges
New Concepts, Ideas and Innovations in Aerospace… 181
equals 4a. If we will take other values the coefficient b will be changed approximately in
50%.
Figure 5. Electrostatic force for 1 m2
via dielectric strength and dielectric coefficient. d is dielectric
coefficient.
Figure 6. Electrostatic force for 1 m2
via safety dielectric strength and dielectric coefficient d.
In our computation we used electric intensity over the electric strength of air Es = 3106
V/m. That means the air located inside of engine between stator and cable can be ionized.
182 Alexander Bolonkin
That is not important because amount of air is small, we can delete (pump) the air from
engine or fill up volume between stator and cable units a good dielectric liquid. We can also
cover the electrodes units a thin dielectric layer having a high voltage dielectric strength.
The data for computations are in Table 1.
Table 1. Properties of various good insulators (recalculated in metric system)
Insulator Resistivity Ohmm
σ107N/m2
Dielectric strength
MV/m. Ei
Dielectric
constant, ε
Tensile strength
kg/mm2
Lexan 1017
–1019 320–640 3 5.5
Kapton H 1019
–1020 120–320 3 15.2
Kel-F 1017
–1019 80–240 2–3 3.45
Mylar 1015
–1016 160–640 3 13.8
Parylene 1017
–1020 240–400 2–3 6.9
Polyethylen e 1018
–51018 40–680* 2 2.8–4.1
Poly (tetra
fluoraethylene)
1015
–51019 40–280** 2 2.8–3.5
Air (1 atm, 1 mm gap) 4 1 0
Vacuum
(1.310–3
Pa1 mm gap)
80–120 1 0
*For room temperature 500–700 MV/m.
** 400–500 MV/m.
Sources: Encyclopedia of Science and Technology (New York, 2002, Vol. 6, p. 104, p. 229, p. 231) and
Kikoin66
, p. 321.
Note: Dielectric constant can reach 4.5 - 7.5 for mica (E is up 200 MV/m), 6 -10 for glasses (E = 40
MV/m), and 900 -3000 for special ceramics (marks are CM-1, T-900)66 , p. 321, (E =13 -28
MV/m). Ferroelectrics have up to 104 - 105. Dielectric strength appreciably depends from
surface roughness, thickness, purity, temperature and other conditions of materials. Very clean
material without admixture (for example, quartz) can have electric strength up 1000 MV/m. For
thin silicon oxide films the calculated results for fields up to 9.5 MV/cm were found to agree well
with measurements for temperatures from -145°C to 65°C and for thicknesses from 3000 Å to 50
000 Å (1966). It is necessary to find good isolative materials and to research conditions which
increase the dielectric strength (Figures 7, 8).
Figure 7. Variation of electric strength with temperature for polyethylene.
New Concepts, Ideas and Innovations in Aerospace… 183
Figure 8. Uniform field dialectric strength for solid, gas and vacuum insulation.
2. The Half-Life of the Charge
Let us estimate of lifetime of charged cable.
(a) Charge in spherical ball. Let us take a very complex condition; where the unlike
charges are separated only by an insulator (charged spherical condenser):
k a
t t
ak
q
q
t
ak
q q
k
a C
RC
dt
q
d q
C
a
d t
d q R
C
q U
a
R
kq
Ri U U E E
h h
4
0.693 0.7, 0.693
2
1
ln 4
,
2
1
,
4
exp
, , 0, , ,
4
0, , ,
0
0
2 2
(6 -7)
where: th – half-life time, [sec]; R – insulator resistance, [Ohm]; i – current, [A]; U – voltage,
[V]; δ – thickness of insulator, [m]; E – electrical intensity, [V/m]; q – charge, [C]; t - time,
[seconds]; ρ – specific resistance of insulator, [Ohm-meter, Ωm]; a – internal radius of the
ball, [m]; C – capacity of the ball, [C]; k = 9109
.
Example: Let us take typical data: ρ =1019 -m, k = 9109
, δ/a = 0.2, then th = 1.24107
seconds = 144 days.
(b) Half-life of cylindrical tube. The computation is same as for tubes (1 m charged
cylindrical condenser):
.
2
, 0, 0.7
2 ln(1 / )
0.693
,
1
, 0.693
2
,
ln 1 /
,
1
0 exp
k
t
a
for
ka a
t
t
a RC
R
k a
t C
RC
q q
h h
h
(8)
184 Alexander Bolonkin
3. Condenser as Accumulator of Launch Energy
Space launcher needs in much energy. Most researchers of the electromagnetic launcher
offer condensers for storage of energy. Let us estimate the maximum energy which can be
accumulated by a 1 kg of a plate electric condenser.
2
2
4
,
4
,
2 8
1
U k d
Q
C
k d
E
M
Q
where Q
k
E W Q U
M
M
s
M
s
M M
(9)
where WM is energy [J/kg], QM is electric charge [C/kg], U is voltage [V], CM is value of
capacitor [C/kg], is specific density of dielectric [kg/m3
], d is distance between plate
(layers) in plate condenser [m].
For = 3, Es =3108 V/m, k = 9109 we have WM = 660 J/kg. That is very small value.
The energy of a gunpowder is about 3 MJ/kg, the energy of a rocket fuel is 9 MJ/kg (C+O2=
CO2). In previous works (see, for example, [25],[40]) the author offered to use as energy
accumulator the fly-wheel. The fly-wheel energy storages is
2
1 WM
(10)
where is safety tensile stress [N/m2
] of fly-wheel material. For = 300 kg/mm2
, = 1800
kg/m3
(it is current composite matter from artificial fibers) we have WM = 0.83105
J/kg.
When we will have composite matter from nanotubes that value increased many times.
The fly-wheel connected with the electrostatic variable frequency rotary motor is shown
in Figure 9.
Figure 9. Variable frequency electrostatic high voltage motor-generator connected with fly wheel for
cable space accelerator. Notation: 1 - rotor with electric charges; 2 - stator of motor with electric
charges; 3 - variable type transmission;; 4 - fly-wheel; 5, 6 - type spools, 7 - type.
This motor has the linear charges located on rotor and stator surface producing high
voltage and variable frequency current (voltage) which is used for producing a running wave
in the cable thruster-accelerator of Figure 2. For compensation of decreasing of fly-wheel
New Concepts, Ideas and Innovations in Aerospace… 185
revolutions and changing of current frequency it is use the variable type transmission (left
part of Figure 9). The type 7 is spooled from spool 6 to spool 5. The diameters of spools 5 - 6
change and speed (revolutions) of rotor also smoothly change.
4. Required Current Frequency
The required current frequency, , can be computed equation
s
V
(11)
where V is wave speed (speed ship, projectile, or shell) [m/s]; s is distance between maximum
and minimum of wave (voltage or opposed charges) [m].
APPLICATIONS
1. Electrostatic Space Launcher. Assume we have project 1 in [23] - [25],[40],[60]
(Figure1a). That is people-carrying space vehicle having mass m = 15 tons and acceleration n
= 3g. For reaching speed V = 8 km/s and 3g acceleration the vehicle needs in thrust of T = 45
tons and distance 1100 km. In [40] it is shown: for conventional cable having safety tensile
stress = 180 kg/mm2
, = 1800 kg/m3 we must have 109 drive stations and cable diameter
19 mm. For 45 ton thrust and electric intensity 3108 V/m the stator (Figure 2e) must have
length 6.7 m. If it uses the cable design (Figure 2f) the stator will be shorter sometimes. For
distance between opposed charges s = 0.1 m the maximum current frequency is 8000/0.1 =
8104
1/s.
It is using the suggested electrostatic linear engine, we can build a cheap high productive
manned (or unmanned) space catapults at present time. This catapult decreases a launch cost
up 2 - 4 $/kg and allows to launch thousands tons in year.
That will be simpler then author's catapult offered in [23]-[25],[40],[60]. Nanotubes
moving cable and the 109 drive stations are not needed. There is only electrostatic motionless
cable-stator (which produces a running electrostatic wave) and linear charged rotor connected
to a spaceship. The cable-stator is suspended on columns (or in air as in [41] - [42]).
Let us to estimate the parameters of new cable launcher for spaceship above. The request
power is P = TV = 45104
8103
= 3.6109 W. For voltage U = 108 V the electric currency
equals I = P/U = 36 A. The 1 mm insulated wire allows a safety permanent electric current
more 11 A/mm2
. The 6 wires inserted in cable are enough for delivering the short maximum
power P to charged sells. We took the maximum speed 8 km/s, the average speed is 4 km/s
and the electric wire will be in two time smaller.
Let us assume the main cable is made from conventional artificial fibers having
maximum tensile stress m = 600 kg/mm2
, Let us take a safety tensile stress = 100 kg/mm2
.
Then the request cross-section cable area is S = T/ = 45000/100 = 450 mm2
, power cable
diameter is d = 24 mm.
186 Alexander Bolonkin
2. Electrostatic Space Propulsion. Assume we want to launch 2 kg interplanetary probe
by 100 m electrostatic accelerator (launcher). We use probe having some sq. meter surface
design (Figure 2f) and thrust 120 tons/m2
(Figure6). Then the acceleration will be
F/M=1,2106
/2 = 0.6106 m/s2
, final speed V = (2102
o.6106
)
0.5 =11 km/s, final frequency
(for s =10 -2 m) = 1.1105
1/s.
3. Transport systems for Space Elevator, Earth-Moon, Earth-Mars. In
[25],[29],[30],[36],[39], [60] the author offered and researched the mechanical cable transport
systems for Space Elevator and for Earth-Moon, Earth-Mars trips. All these systems need in
high speed engine for moving of space vehicle. One (cable) version of the suggested transport
system is noted in above cited works. However, the system offered in given article may be
used in many structures. The cable is stator, the vehicle has linear rotor. The cable delivers
the energy in form of running wave, the vehicle (climber) follows this running wave. The
speed of running wave (vehicle) can be very high. The voltage is extremely big and a weight
of the electric wires is small.
Let us to make the simplest estimation. Assume, the climber weights W = 1 ton = 10,000
N and has speed V = 1 km/s = 1000 m/s. The power is P = WV = 104
103
= 107 W. For
voltage U = 108 V, the electric currency is i = 107
/108
=0.1 A. For safety currency 20 A/mm2
,
the need wire diameter is about 0.1 mm2
.
4. Suspended satellite system. In [25],[36] the author suggested the cable ring rotated
around the Earth with motionless satellites suspended to the ring (Figure1e). The offered
linear engine can be used as engine for compensation the air friction of cable and as noncontact
bearing for suspend system.
5. Electrostatic levitation train and linear engine. In [59] the author suggested the
electrostatic levitation train (Figure1g). The offered linear engine can be used as propulsion
engine for this train. In braking the energy of acceleration will be returned in electric line.
6. Electrostatic rotary engine. At present time industry uses conventional low voltage
electric engine. When we have a high voltage electric line it may be easier to use high voltage
electrostatic rotary engine.
7. Electrostatic levitation bearing. Some technical installations need low friction
bearings. The mono-electrets can be used as non-contact bearing having zero mechanical
friction.
8. Electrostatic Gun System. The armor cannonry needs in high speed shells. However,
the shell speed is limited by gas speed into cannon. The suggested linear electrostatic engine
can be used as the high efficiency shells in armor-piercing cannonry having very high initial
shell speed because the initial shell speed of linear engine does not have the speed limit (see
application 1 above). That means the electrostatic gun can shoot in thousands kilometers.
CONCLUSION
The offered electrostatic engine could find wide application in many fields of technology.
That can decrease the launch cost from hundreds to thousands times. The electrostatic engine
needs a very high voltage but this voltage is located in small area inside of installations and
not dangerous to people. The current technology does not have another way for reaching a
New Concepts, Ideas and Innovations in Aerospace… 187
high speed except may be rockets. But rockets and rocket launches are very expensive and we
do not know ways to decrease the cost of rocket launch thousand times.
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: 'Bolonkin', and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 ps.)
[1] Bolonkin, A.A., (1965a), ―Theory of Flight Vehicles with Control Radial Force‖.
Collection Researches of Flight Dynamics, Mashinostroenie Publisher, Moscow, , pp.
79-118, 1965, (in Russian). Intern.Aerospace Abstract A66-23338#(Eng).
[2] Bolonkin A.A., (1965c), Optimization of Trajectories of Multistage Rockets. Collection
Researches of Flight Dynamics. Moscow, 1965, p. 20 -78 (in Russian). International
Aerospace Abstract A66-23337# (English).
[3] Bolonkin, A.A., (1982a), Installation for Open Electrostatic Field, Russian patent
application #3467270/21 116676, 9 July, 1982 (in Russian), Russian PTO.
[4] Bolonkin, A.A., (1982b), Radioisotope Propulsion. Russian patent application
#3467762/25 116952, 9 July 1982 (in Russian), Russian PTO.
[5] Bolonkin, A.A., (1982c), Radioisotope Electric Generator. Russian patent application
#3469511/25 116927. 9 July 1982 (in Russian), Russian PTO.
[6] Bolonkin, A.A., (1983a), Space Propulsion Using Solar Wing and Installation for It,
Russian patent application #3635955/23 126453, 19 August, 1983 (in Russian), Russian
PTO.
[7] Bolonkin, A.A., (1983b), Getting of Electric Energy from Space and Installation for It,
Russian patent application #3638699/25 126303, 19 August, 1983 (in Russian), Russian
PTO.
[8] Bolonkin, A.A., (1983c), Protection from Charged Particles in Space and Installation
for It, Russian patent application #3644168 136270, 23 September 1983, (in Russian),
Russian PTO.
[9] Bolonkin, A. A., (1983d), Method of Transformation of Plasma Energy in Electric
Current and Installation for It. Russian patent application #3647344 136681 of 27 July
1983 (in Russian), Russian PTO.
[10] Bolonkin, A. A., (1983e), Method of Propulsion using Radioisotope Energy and
Installation for It. of Plasma Energy in Electric Current and Installation for it. Russian
patent application #3601164/25 086973 of 6 June, 1983 (in Russian), Russian PTO.
[11] Bolonkin, A. A.,(1983f), Transformation of Energy of Rarefaction Plasma in Electric
Current and Installation for it. Russian patent application #3663911/25 159775, 23
November 1983 (in Russian), Russian PTO.
[12] Bolonkin, A. A., (1983g), Method of a Keeping of a Neutral Plasma and Installation
for it. Russian patent application #3600272/25 086993, 6 June 1983 (in Russian),
Russian PTO.
[13] Bolonkin, A.A.,(1983h), Radioisotope Electric Generator. Russian patent application
#3620051/25 108943, 13 July 1983 (in Russian), Russian PTO.
188 Alexander Bolonkin
[14] Bolonkin, A.A., (1983i), Method of Energy Transformation of Radioisotope Matter in
Electricity and Installation for it. Russian patent application #3647343/25 136692, 27
July 1983 (in Russian), Russian PTO.
[15] Bolonkin, A.A., (1983j), Method of stretching of thin film. Russian patent application
#3646689/10 138085, 28 September 1983 (in Russian), Russian PTO.
[16] Bolonkin, A.A., (1987), ―New Way of Thrust and Generation of Electrical Energy in
Space‖. Report ESTI, 1987, (Soviet Classified Projects).
[17] Bolonkin, A.A., (1990), ―Aviation, Motor and Space Designs‖, Collection Emerging
Technology in the Soviet Union, 1990, Delphic Ass., Inc., pp.32-80 (English).
[18] Bolonkin, A.A., (1991), The Development of Soviet Rocket Engines, 1991, Delphic
Ass.Inc.,122 p. Washington, (in English).
[19] Bolonkin, A.A., (1992a), ―A Space Motor Using Solar Wind Energy (Magnetic Particle
Sail)”. The World Space Congress, Washington, DC, USA, 28 Aug. - 5 Sept., 1992,
IAF-0615.
[20] Bolonkin, A.A., (1992b), ―Space Electric Generator, run by Solar Wing‖. The World
Space Congress, Washington, DC, USA, 28 Aug. -5 Sept. 1992, IAF-92-0604.
[21] Bolonkin, A.A., (1992c), ―Simple Space Nuclear Reactor Motors and Electric
Generators Running on Radioactive Substances‖, The World Space Congress,
Washington, DC, USA, 28 Aug. - 5 Sept., 1992, IAF-92-0573.
[22] Bolonkin, A.A. (1994), “The Simplest Space Electric Generator and Motor with
Control Energy and Thrust”, 45th International Astronautical Congress, Jerusalem,
Israel, 9-14 Oct., 1994, IAF-94-R.1.368 .
[23] Bolonkin, A.A., (2002a), “Non-Rocket Space Rope Launcher for People‖, IAC-02-
V.P.06, 53rd International Astronautical Congress, The World Space Congress - 2002,
10-19 Oct 2002, Houston, Texas, USA.
[24] Bolonkin, A.A,(2002b), ―Non-Rocket Missile Rope Launcher‖, IAC-02-IAA.S.P.14,
53rd International Astronautical Congress, The World Space Congress - 2002, 10-19
Oct 2002, Houston, Texas, USA.
[25] Bolonkin, A.A.,(2002c), ―Inexpensive Cable Space Launcher of High Capability‖, IAC02-V.P.07,
53rd International Astronautical Congress, The World Space Congress -
2002, 10-19 Oct 2002, Houston, Texas, USA.
[26] Bolonkin, A.A.,(2002d), ―Hypersonic Launch System of Capability up 500 tons per day
and Delivery Cost $1 per Lb‖. IAC-02-S.P.15, 53rd International Astronautical
Congress, The World Space Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[27] Bolonkin, A.A.,(2002e), ―Employment Asteroids for Movement of Space Ship and
Probes‖. IAC-02-S.6.04, 53rd International Astronautical Congress, The World Space
Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[28] Bolonkin, A.A., (2002f), ―Optimal Inflatable Space Towers of High Height‖. COSPAR02
C1.1-0035-02, 34th Scientific Assembly of the Committee on Space Research
(COSPAR), The World Space Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[29] Bolonkin, A.A., (2002g), “Non-Rocket Earth-Moon Transport System‖, COSPAR-02
B0.3-F3.3-0032-02, 02-A-02226, 34th Scientific Assembly of the Committee on Space
Research (COSPAR), The World Space Congress - 2002, 10-19 Oct 2002, Houston,
Texas, USA.
New Concepts, Ideas and Innovations in Aerospace… 189
[30] Bolonkin, A. A.,(2002h) ―Non-Rocket Earth-Mars Transport System‖, COSPAR-02
B0.4-C3.4-0036-02, 34th Scientific Assembly of the Committee on Space Research
(COSPAR), The World Space Congress - 2002, 10-19 Oct 2002, Houston, Texas, USA.
[31] Bolonkin, A.A.,(2002i). ―Transport System for Delivery Tourists at Altitude 140 km‖.
IAC-02-IAA.1.3.03, 53rd International Astronautical Congress, The World Space
Congress - 2002, 10-19 Oct. 2002, Houston, Texas, USA.
[32] Bolonkin, A.A., (2002j), ‖Hypersonic Gas-Rocket Launch System.‖ AIAA-2002-3927,
38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 7-10 July
2002. Indianapolis, IN, USA.
[33] Bolonkin, A.A., (2003a), ―Air Cable Transport‖, Journal of Aircraft, Vol. 40, No. 2,
March-April 2003.
[34] Bolonkin, A.A., (2003b), ―Optimal Inflatable Space Towers with 3-100 km Height‖,
JBIS, Vol. 56, No 3/4, pp. 87-97, 2003.
[35] Bolonkin, A.A.,(2003c), ―Asteroids as Propulsion Systems of Space Ships‖, JBIS, Vol.
56, No 3/4, pp. 97-107, 2003.
[36] Bolonkin A.A., (2003d), ―Non-Rocket Transportation System for Space Travel‖, JBIS,
Vol. 56, No 7/8, pp. 231-249, 2003.
[37] Bolonkin A.A., (2003e), ―Hypersonic Space Launcher of High Capability‖, Actual
problems of aviation and aerospace systems, Kazan, No. 1(15), Vol. 8, 2003, pp. 45-58.
[38] Bolonkin A.A., (2003f), ―Centrifugal Keeper for Space Stations and Satellites‖, JBIS,
Vol. 56, No 9/10, pp. 314-327, 2003.
[39] Bolonkin A.A., (2003g), ―Non-Rocket Earth-Moon Transport System‖, Advances in
Space Research, Vol. 31/11, pp. 2485-2490, 2003, Elsevier.
[40] Bolonkin A.A., (2003h), ―Earth Accelerator for Space Ships and Missiles‖. JBIS, Vol.
56, No. 11/12, 2003, pp. 394-404.
[41] Bolonkin A.A., (2003i), ―Air Cable Transport and Bridges‖, TN 7567, International Air
and Space Symposium - The Next 100 Years, 14-17 July 2003, Dayton, Ohio, USA.
[42] Bolonkin, A.A., (2003j), ―Air Cable Transport System‖, Journal of Aircraft, Vol. 40,
No. 2, March-April 2003, pp. 265-269.
[43] Bolonkin A.A.,(2004a), ―Kinetic Space Towers and Launchers ‗, JBIS, Vol. 57, No 1/2,
pp. 33-39, 2004.
[44] Bolonkin A.A.,(2004b), ―Optimal trajectory of air vehicles‖, Aircraft Engineering and
Space Technology, Vol. 76, No. 2, 2004, pp. 193-214.
[45] Bolonkin A.A., (2004c), ―Long Distance Transfer of Mechanical Energy‖, International
Energy Conversion Engineering Conference at Providence RI, Aug. 16-19, 2004,
AIAA-2004-5660.
[46] Bolonkin, A.A., (2004d), ―Light Multi-Reflex Engine‖, Journal JBIS, Vol. 57, No 9/10,
pp. 353-359, 2004.
[47] Bolonkin, A.A., (2004e), ―Kinetic Space Towers and Launchers‖, Journal JBIS, Vol.
57, No 1/2, pp. 33-39, 2004.
[48] Bolonkin, A.A., (2004f), ―Optimal trajectory of air and space vehicles‖, AEAT, No 2,
pp. 193-214, 2004.
[49] Bolonkin, A.A.,(2004g), ―Hypersonic Gas-Rocket Launcher of High Capacity‖,
Journal JBIS, Vol. 57, No 5/6, pp. 167-172, 2004.
190 Alexander Bolonkin
[50] Bolonkin, A.A., (2004h), ―High Efficiency Transfer of Mechanical Energy‖.
International Energy Conversion Engineering Conference at Providence RI, USA. 16-
19 August, 2004, AIAA-2004-5660.
[51] Bolonkin, A.A., (2004i), ―Multi-Reflex Propulsion System for Space and Air
Vehicles‖, JBIS, Vol. 57, No 11/12, 2004, pp. 379-390.
[52] Bolonkin A.A.,(2005a) ―High Speed Catapult Aviation‖, AIAA-2005-6221,
Atmospheric Flight Mechanic Conference - 2005, 15-18 August, 2005, USA.
[53] Bolonkin A.A., (2005a), Electrostatic Solar Wind Propulsion System, AIAA-2005-
3653. 41-st Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[54] Bolonkin A.A., (2005b), Electrostatic Utilization of Asteroids for Space Flight, AIAA2005-4032.
41 Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[55] Bolonkin A.A., (2005c), Kinetic Anti-Gravitator, AIAA-2005-4504. 41-st Propulsion
Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[56] Bolonkin A.A., (2005d), Sling Rotary Space Launcher, AIAA-2005-4035. 41-st
Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[57] Bolonkin A.A., (2005e), Radioisotope Space Sail and Electric Generator, AIAA-2005-
4225. 41-st Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[58] Bolonkin A.A., (2005f), Guided Solar Sail and Electric Generator, AIAA-2005-3857.
41-st Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[59] Bolonkin A.A., (2005g), Problems of Electrostatic Levitation and Artificial Gravity,
AIAA-2005-4465. 41 Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[60] Bolonkin A.A., (2006a), "Non-Rocket Space Launch and Flight", Elsevier, London,
2006, 488 pgs..
[61] Bolonkin A.A., (2006b), Electrostatic AB-Ramjet Space Propulsion, AIAA-2006-6173,
http://arxiv.org, search: "Bolonkin".
[62] Bolonkin A.A., (2006c), Beam Space Propulsion, AIAA-2006-7492, http://arxiv.org,
search: "Bolonkin".
[63] Bolonkin A.A., (2006d), High Speed Solar Sail, AIAA-2006-4806, (http://arxiv.org,
search: "Bolonkin".
[64] Bolonkin A.A., (2006e), Suspended Air Surveillance System, AIAA-2006-6511,
http://arxiv.org, search: "Bolonkin".
[65] Bolonkin A.A., (2006f), Optimal Solid Space Tower (Mast), http://arxiv.org, search:
"Bolonkin".
[66] Kikoin, I.K., (ed.), Tables of physical values. Atomuzdat, Moscow, 1976 (in Russian).
New Concepts, Ideas and Innovations in Aerospace… 191
Pictures for Part A, Ch. 10. Possible electrostatic launchers
192 Alexander Bolonkin
Chapter 11
Optimal Electrostatic Space Tower
(Mast, New Space Elevator)*
Abstract
Author offers and researched the new and revolutionary inflatable electrostatic AB
space towers (mast, new space elevator) up to one hundred twenty thousands kilometers
(or more) in height.
The main innovation is filling the tower by electron gas, which can create pressure
up one atmosphere, has negligible small weight and surprising properties.
The suggested mast has following advantages in comparison with conventional
space elevator:
1. Electrostatic AB tower may be built from Earth's surface without the employment
of any rockets. That decreases the cost of electrostatic mast by thousands of times. 2. One
can have any height and has a big control load capacity. 3. Electrostatic tower can have
the height of a geosynchronous orbit (36,000 km) WITHOUT the additional top cable as
the space elevator (up 120,000 160,000 km) and counterweight (equalizer) of hundreds
of tons. 4. The offered mast has less total mass than conventional space elevator. 5. The
offered mast can be built from less strong material than space elevator cable. 6. The
offered tower can have the high-speed electrostatic climbers moved by high-voltage
electricity from Earth's surface. 7. The offered tower is safer resisting meteorite strikes
than an ordinary cable space elevator. 8. The electrostatic mast can bend in any needed
direction when we give the necessary electric voltage in the required parts of the
extended mast. 9. Control mast has stability for any altitude. Three projects 100 km,
36,000km (GEO), 120,000 km are computed and presented.
These towers can be used for tourism, scientific observation of space, observation of
the Earth‘s surface, weather and upper atmosphere experiments, and for radio, television,
and communication transmissions. These towers can also be used to launch interplanetary
spaceships and Earth-orbiting satellites.
Key words: Space tower, electrostatic space mast, space tourism, space communication,
space launch, space observation
New Concepts, Ideas and Innovations in Aerospace… 193
Presented as Bolonkin's paper AIAA-2007-6201 to 43-rd AIAA Joint Propulsion Conference, 8-
11 July 2007, Cincinnati, OH, USA.
Introduction
Brief History. The idea of building a tower high above the Earth into the heavens is very old
[1]. The writings of Moses, in chapter 11 of his book Genesis refers to an early civilization
that tried to build a tower to heaven out of brick and tar. This construction was called the
Tower of Babel, and was reported to be located in Babylon in ancient Mesopotamia. Later in
chapter 28, Jacob had a dream about a staircase or ladder built to heaven. This construction
was called Jacob‘s Ladder. More contemporary writings on the subject date back to K.E.
Tsiolkovski in his manuscript ―Speculation about Earth and Sky and on Vesta,‖ published in
1895 [2]. This idea inspired Sir Arthur Clarke to write his novel, The Fountains of Paradise
[3], about a space tower (elevator) located on a fictionalized Sri Lanka, which brought the
concept to the attention of the entire 20th Century world.
Today, the world‘s tallest construction is a television transmitting tower (mast) near
Fargo, North Dakota, USA. It stands 629 m high and was built in 1963 for KTHI-TV. The
CNN Tower in Toronto, Ontario, Canada is the world‘s tallest building. It is 553 m in height,
was completed in1975, and has the world‘s highest observation deck at 447 m. The tower
structure is concrete up to the observation deck level. Above is a steel structure supporting
radio, television, and communication antennas. The total weight of the tower is 3,000,000
metric tons.
The Ostankin Tower in Moscow is 540 m in height and has an observation desk at 370
m. The world‘s tallest office building is the Petronas Towers in Kuala Lumpur, Malasia. The
twin towers are 452 m in height. They are 10 m taller than the Sears Tower in Chicago,
Illinois, USA. The Skyscrapers (Taipei, Taiwan, 2004) has height of 509 m, the Eiffel Tower
(Paris, 1887-1889) has 300 m, Empire State Building (USA, New York, 1930-1931) has 381
m + TV mast of 61 m. Under construction a building of 1001 m (Kuwait City, Kuwait) and
1430 m Supported Structure in Gulf of Mexico.
Current materials make it possible even today to construct towers many kilometers in
height. However, conventional towers are very expensive, costing billions of dollars. When
considering how high a tower can be built, it is important to remember that it can be built to
high height if the base is large enough. Theoretically, you could build a tower to
geosynchronous Earth orbit (GEO) out of bubble gum, but the base would likely cover half
the surface of the Earth.
The new types of towers. The author offered and researched a series on new towers
(masts) [6]-[11]: optimal inflatable towers filled by gas (air, helium, hydrogen), optimal solid
towers, new kinetic cable towers.
The offering new revolutionary electrostatic tower is based on old (1982) ideas author
of using electrostatic forces [4]-[5]. They are applied to space tower and are shown the
gigantic advantages in comparison with conventional space elevator. Some of these
advantages named in abstract over. Main of them are follow: electrostatic mast can be built
any height without rockets, one needs material in tens times less them space elevator. That
means the electrostatic mast will be in hundreds times cheaper then conventional space
194 Alexander Bolonkin
elevator. One can be built on the Earth‘s surface and their height can be increased as
necessary. Their base is very small.
The main innovations in this project are the application of electron gas for filling tube at
high altitude and a solution of a stability problem for tall (thin) inflatable mast by control
structure.
The tower applications. The high towers (3-100 km) have numerous applications for
government and commercial purposes:
Entertainment and Observation platform.
Entertainment and Observation desk for tourists. Tourists could see over a huge area,
including the darkness of space and the curvature of the Earth‘s horizon.
Drop tower: tourists could experience several minutes of free-fall time. The drop tower
could provide a facility for experiments.
A permanent observatory on a tall tower would be competitive with airborne and orbital
platforms for Earth and space observations.
Communication boost: A tower tens of kilometers in height near metropolitan areas could
provide much higher signal strength than orbital satellites.
Solar power receivers: Receivers located on tall towers for future space solar power
systems would permit use of higher frequency, wireless, power transmission systems
(e.g. lasers).
Low Earth Orbit (LEO) communication satellite replacement: Approximately six to ten
100-km-tall towers could provide the coverage of a LEO satellite constellation with
higher power, permanence, and easy upgrade capabilities.
The towers having a height 36,000 120,000 km may be used for free launching the
Earth's satellites and interplanetary ships and as space station for arriving space ships.
Other new revolutionary methods of access to space are described in [10]-[14].
Description of Installation and Innovations
1. Electrostatic tower. The offered electrostatic space tower (or mast, or space
elevator) is shown in fig.1. That is inflatable cylinder (tube) from strong thin dielectric film
having variable radius. The film has inside the sectional thin conductive layer 9. Each section
is connected with issue of control electric voltage. In inside the tube there is the electron gas
from free electrons. The electron gas is separated by in sections by a thin partition 11. The
layer 9 has a positive charge equals a summary negative charge of the inside electrons. The
tube (mast) can have the length (height) up Geosynchronous Earth Orbit (GEO, about 36,000
km) or up 120,000 km (and more) as in our project (see computation below). The very high
tower allows to launch free (without spend energy in launch stage) the interplanetary space
ships. The offered optimal tower is design so that the electron gas in any cross-section area
compensates the tube weight and tube does not have compressing longitudinal force from
weight. More over the tower has tensile longitudinal (lift) force which allows the tower has a
vertical position. When the tower has height more GEO the additional centrifugal force of the
rotate Earth provided the vertical position and natural stability of tower.
The bottom part of tower located in troposphere has the bracing wires 4 which help the
tower to resist the troposphere wind.
New Concepts, Ideas and Innovations in Aerospace… 195
The control sectional conductivity layer allows to create the high voltage running wave
which accelerates (and brakes) the cabins (as rotor of linear electrostatic engine [11]) to any
high speed. Electrostatic forces also do not allow the cabin to leave the tube.
2. Electron gas and AB tube. The electron gas consists of conventional electrons. In
contract to molecular gas the electron gas has many surprising properties. For example,
electron gas (having same mass density) can have the different pressure in the given volume.
Its pressure depends from electric intensity, but electric intensity is different in different part
of given volume (fig.2b). For example, in our tube the electron intensity is zero in center of
cylindrical tube and maximum at near tube surface.
The offered AB-tube is main innovation in the suggested tower. One has a positive
control charges isolated thin film cover and electron gas inside. The positive cylinder
Fig.1. Electrostatic AB tower (mast, Space Elevator). (a) Side view, (b) Cross-section along axis,
(c) Cross-section wall perpendicular axis. Notation: 1 - electrostatic AB tower (mast, Space
Elevator); 2 - Top space station; 3 - passenger, load cabin with electrostatic linear engine; 4
- bracing (in troposphere); 5 - geosynchronous orbit; 6 - tensile force from electron gas; 7 -
Earth; 8 - external layer of isolator; 9 - conducting control layer having sections; 10 -
internal layer of isolator; 11 - internal dielectric partition; 12 - electron gas, 13 - laser
control beam.
create the zero electric field inside the tube and electron conduct oneself as conventional
molecules that is equal mass density in any points. When kinetic energy of electron is less
then energy of negative ionization of the dielectric cover or the material of the electric cover
does not accept the negative ionization, the electrons are reflected from cover. In other case
the internal cover layer is saturated by negative ions and begin also to reflect electrons.
Impotent also that the offered AB electrostatic tube has neutral summary charge in outer
space.
Advantages of electrostatic tower. The offered electrostatic tower has very important
advantages in comparison with space elevator:
1. Electrostatic AB tower (mast) may be built from Earth's surface without rockets.
That decreases the cost of electrostatic mast in thousands times.
196 Alexander Bolonkin
2. One can have any height and has a big control load capacity.
3. In particle, electrostatic tower can have the height of a geosynchronous orbit (37,000
km) WITHOUT the additional continue the space elevator (up 120,000 160,000
km) and counterweight (equalizer) of hundreds tons [10], Ch.1.
4. The offered mast has less the total mass in tens of times then conventional space
elevator.
5. The offered mast can be built from lesser strong material then space elevator cable
(comprise the computation here and in [10] Ch.1).
6. The offered tower can have the high speed electrostatic climbers moved by high
voltage electricity from Earth's surface.
7. The offered tower is more safety against meteorite then cable space elevator, because
the small meteorite damaged the cable is crash for space elevator, but it is only create
small hole in electrostatic tower. The electron escape may be compensated by
electron injection.
8. The electrostatic mast can bend in need direction when we give the electric voltage in
need parts of the mast.
The electrostatic tower of height 100 500 km may be built from current artificial
fiber material in present time. The geosynchronous electrostatic tower needs in more
strong material having a strong coefficient K ≥ 2 (whiskers or nanotubes, see below).
3. Other applications of offered AB tube idea.
The offered AB-tube with the positive charged cover and the electron gas inside may
find the many applications in other technical fields. For example:
1) Air dirigible. (1) The airship from the thin film filled by an electron gas has 30%
more lift force then conventional dirigible filled by helium. (2) Electron dirigible is
significantly cheaper then same helium dirigible because the helium is very
expensive gas. (3) One does not have problem with changing the lift force because
no problem to add or to delete the electrons.
2) Long arm. The offered electron control tube can be used as long control work arm for
taking the model of planet ground, rescue operation, repairing of other space ships
and so on [10] Ch.9.
3) Superconductive or closed to superconductive tubes. The offered AB-tube must have
a very low electric resistance for any temperature because the electrons into tube to
not have ions and do not loss energy for impacts with ions. The impact the electron
to electron does not change the total impulse (momentum) of couple electrons and
electron flow. If this idea is proved in experiment, that will be big breakthrough in
many fields of technology.
4) Superreflectivity. If free electrons located between two thin transparency plates, that
may be superreflectivity mirror for widely specter of radiation. That is necessary in
many important technical field as light engine, multy-reflect propulsion [10] Ch.12
and thermonuclear power [15].
The other application of electrostatic ideas is Electrostatic solar wind propulsion [10]
Ch.13, Electrostatic utilization of asteroids for space flight [10] Ch.14, Electrostatic levitation
on the Earth and artificial gravity for space ships and asteroids [14, 10 Ch.15], Electrostatic
solar sail [10] Ch.18, Electrostatic space radiator [10] Ch.19, Electrostatic AB ramjet space
propulsion [14], etc.
Theory and Computation
New Concepts, Ideas and Innovations in Aerospace… 197
Below reader find the evidence of main equations, estimations, and computations.
1. Optimal radius (cross-section) area of tower. Assume we have tower from thin film
filled by electron gas. Take the thin ring of tower cover with dH height (Fig.2a). For getting
the optimal radius the weight (force in N) gdL of this elementary ring must be support by
electron gas pressure pdr. From projection of force on vertical axis we have
pdr g dL, dL dH, pdr gdH, (1)
where p is electron (charge) pressure, N/m2
; dr and dH is elementary radius and tower
height respectively (see fig.2), m; g is Earth gravity at altitude H, m/s2
; is cover density,
kg/m3
; is cover thickness, m.
The gravity for rotated Earth and electron (charge) pressure are (see [10] Ch.1)
2
,
2
0
0
2
2
2
0
0
E
p
g
R
R
R
g g
. (2)
where g0 = 9.81 m/s2
is Earth's gravity at altitude H = 0; R0 = 6378 km is radius of Earth,
m; R = R0 + H is distance from given cross-section tower to center of Earth, m; = 72.685
10 -6
rad/s is angle speed of the Earth; E is maximum electric intensity, V/m (fig.2b); 0 =
8.8510 -12 F/m is electrostatic constant.
Fig. 2. (a) For explanation of theory optimal cross-section area of the electrostatic AB tower.
(b) graph of electric intensity into tower
Look your attention that electron gas is different from conventional molecular gas.
That can have a different electric intensity (that means a different pressure!) in different place
of volume. The electron pressure equals zero in axis of tube and one is maximum at
maximum radius of tube.
In optimal tower the electronic pressure must keep the cover
198 Alexander Bolonkin
2
or
2
2 2 or or
2
0
2
0 E
r
rp r E
rpdL d L , (3)
Substitute (2)-(3) in (1) and integrate we receive
1
2
1 1
exp 2
0
2
0
2
0
2
0 0
0
0
2
2
2
0 0
0 0
R
R
k R R g
g R
r
r
o r r
d R
g
R
R
R
k
g
r
d r R
R
r
r
, (4)
where k = / is coefficient relative strength, m/s, K = k/107
.
The computation equation (4) via H for different K are presented in fig. 3.
As you see than more a relative strength of cover then is more the tower diameter at
geosynchronous orbit (36,000 km) and then more the lift force of tower everywhere at H for
given p. In difference of space elevator the electrostatic AB tower may be built for small K <
2. But the ratio So/Sgco in this case is big (here S is area of tower base and cross-section area of
tower at geosynchronous orbit respectively).
2. Material strength. Let us consider the following experimental and industrial fibers,
whiskers, and nanotubes [16]-[19]:
Fig. 3. Relative radius of electrostatic tower versus height and strong of cover film. K =
k/107
.
Experimental nanotubes CNT (carbon nanotubes) have a tensile strength of 200 Giga1.
Pascals (20,000 kg/mm2
). Theoretical limit of nanotubes is 30,000 kg/mm2
.
New Concepts, Ideas and Innovations in Aerospace… 199
2. Young‘s modulus is over 1 Tera Pascal, specific density = 1800 kg/m3
(1.8 g/c3
) (year
2000).
For safety factor n = 2.4, = 8300 kg/mm2 = 8.3×1010 N/m2
, =1800 kg/m3
, k = (/) =
46×106
, K = 4.6. The SWNTs nanotubes have a density of 0.8 g/cm3
, and MWNTs
have a density of 1.8 g/cm3
(average 1.34 g/cm3
). Unfortunately, the nanotubes are very
expensive at the present time. They cost is about $100 g (2004).
3. For whiskers CD = 8000 kg/mm2
, = 3500 kg/m3
(1989) [16 or 10, p. 33], n = 1,
Kmax = 2.37. Cost is about $400/kg (2001).
4. For industrial fibers = 500 600 kg/mm2
, = 1800 kg/m3
, = 2,78×106
, n =1, Kmax
= 0.28. Cost is about 2 5 $/kg (2003).
Figures for some other experimental whiskers and industrial fibers are given in Part
A, Ch. 1, Table 2. See also Reference [10] p. 33.
4. Useful lift force. The useful (tensile) lift force of AB tower may be computed by
equation
2
2
0
0
2 2
0
2
0
2
2 0
0
4
,
4
,
2 4
1
, r
E
S
F
r r F
E
F
E
F pa S r pa p
,(5)
where F if lift force, N; pa is average electron pressure, N/m2
; S = r
2
is cross-section
area of tower, m2
; S0 is base cross-section area, m2
; ro is base radius of tower, m.
The last equation in (5) and many over further equations are more general and
suitable for common case. However, we make computation for base tower radius only 10
m. In this case the reader see the real (non relative) data, which allow him to better
understand the possibility of electrostatic tower. If the lift force is small, it may be
increased by increasing the tower base area.
The computation lift force via altitude for different E, K = 2 and base r0 =10 m is
presented in fig.4.
200 Alexander Bolonkin
Fig. 4. Tower lift force versus tower height for different electric intensity and base radius ro = 10
m and strength coefficient K = 2.
As you see for the electric intensity E = 100 MV (the dielectric thin film can keep E =
700 MV, see Part A, Ch.1, Table 2) the electrostatic tower can keep 5 tons if one has altitude
at geosynchronous orbit and more 100 tons if one has an altitude 120,000 km.
4. Dielectric strength of insulator. As you see above the tower need in film which
separate the positive charges located in conductive layer from the electron gas located into
tube. This film must have a high dielectric strength. The current material can keep a high E
(see Part A, Ch.10, Table 1 and [10]).
Sources: Encyclopedia of Science & Technology (New York, 2002, Vol. 6, p. 104, p.
229, p. 231) and Kikoin [17] p. 321.
Note: Dielectric constant can reach 4.5 - 7.5 for mica (E is up 200 MV/m), 6 -10 for
glasses (E = 40 MV/m), and 900 - 3000 for special ceramics (marks are CM-1, T-900) [17], p.
321, (E =13 - 28 MV/m). Ferroelectrics have up to 104
- 105
. Dielectric strength appreciably
depends from surface roughness, thickness, purity, temperature and other conditions of
materials. Very clean material without admixture (for example, quartz) can have electric
strength up 1000 MV/m. As you see we have a needed dielectric material, but it is necessary
to find good (and strength) isolative materials and to research conditions which increase the
dielectric strength.
5. Tower cover thickness. The thickness of tower cover may be found from Equation
(3). The result of computation is presented in Fig. 5.
6. Mass of tower cover. The mass of tower cover is
New Concepts, Ideas and Innovations in Aerospace… 201
H H H
r d H
k
E
S
M
r d H o r M
k
E r
r d H
k
pr
M
d M r d H
0
2
2
0
0 0
2
0
2
0
2
2 0
2
2 0
2 ,
(6)
where M is cover mass, kg; S0 = ro
2
is tower base area, m2
; p is Eq. (2).
Result of computation is presented in fig. 6.
As you see the total mass of 120,000 km electrostatic tower is about 10,000 tons.
Compare this number with 3,000,000 tons which has the CNN solid tower in Toronto
(Canada) having only 553 m of height.
Fig. 5. Thickness of tower cover versus tower height for different electric intensity and base
radius ro = 10 m and strength coefficient K = 2.
202 Alexander Bolonkin
Fig. 6. Mass of tower cover versus tower height for a different electric intensity and base
radius ro = 10 m and strong coefficient K = 2.
7. The volume V and surface of tower s are
H H
d V r d H V r r d H d s r rd H s r rd H
0
0 0
0
2 2
0
2
, , 2 , , (7)
where V is tower volume, m3
; s is tower surface, m2
.
8. Relation between tower volume charge and tower liner charge is
2
2
0 0
, , ,
2
,
2 r
E E r
r
E
r
EV s V s
, (8)
where is tower volume charge, C/m3
; is tower linear charge, C/m.
9. General charge of tower. We got equation from
H H
rdH
r
Q
Er dQ dH Q Er rdH Q
0
0
0 0
20
, , 20 0
, 2
,(9)
where Q is total tower charge, C; is dielectric constant (see Table 2).
The computation of total charge is shown in fig. 7.
New Concepts, Ideas and Innovations in Aerospace… 203
Fig. 7. Electric charge of tower versus tower height for different electric intensity and base
radius ro = 10 m and strength coefficient K = 2.
10. Charging energy. The charged energy is computed by equation
W 0.5QU, U E, W 0.5Q a E , (10)
where W is charge energy, J; U is voltage, V. For E = 100 MV, H = 120,000 km, Q =
12105 C, a = 510 -7 m the charged energy is 30 MJ.
11. Mass of electron gas. The mass of electron gas is
e
Q Me
meN me
, (11)
where Me
is mass of electron gas, kg; me = 9.1110 -31 kg is mass of electron; N is number
of electrons, e = 1.610 -19 is the electron charge, C.
The computation for our case give Me = 10 -5
kg. That is very small value for
gigantic tower-tube 120 thousands km of height.
12. Power for support of charge. Leakage current (power) through the cover may be
estimated by equation
2
0
, , , ,
sE W IU sE I
s
R
r E
U E
R
U
I l
(12)
where I is electric currency, A; U is voltage, V; R is electric resistance, Ohm; is
specific resistance, Ohm.m; s is tower surface area, m2
.
The estimation gives the support power about 0.1 1 kW.
13. Electron gas pressure. The electron gas pressure may be computed by equation (2). This
computation is presented in fig. 8.
204 Alexander Bolonkin
Fig. 8. Electron pressure versus electric intensity
As you see the electron pressure reach 0.5 atm for an electric intensity 150 MV/m and
for negligibly small mass of the electron gas.
Project
As the example (not optimal design!) we take three electrostatic towers having: the base
(top) radius r0 = 10 m; K = 2; heights H = 100 km, 36,000 km (GEO), and H = 120.000 km
(that may be one tower having named values at given altitudes); electric intensity E = 100
MV/m and 150 MV/m. The results of estimation are presented in Table 1.
Table 1. The results of estimation main parameters of three AB towers (masts)
having the base radius r0 = 100 m and strength coefficient K = 2
for two E =100, 150 MV/m.
Value E MV/m H=100 km H=36,000 km H=120,000 km
Top Radius , m - 99 10 40
Useful lift force, ton 100 1710 3
174 2.710 3
Useful lift force, ton 150 3910 3
390 6.210 3
Relative cover
thickness, δ/r
100 2.210 -6
2.210 -6
2.210 -6
Relative cover
thickness, δ/r
150 510 -6
510 -6
510 -6
Mass of cover, ton 100 1410 3
3105
1106
New Concepts, Ideas and Innovations in Aerospace… 205
Mass of cover, ton 150 31.510 3
1106
2106
Electric charge, C 100 1.1105
3106
12106
Electric charge, C 150 1.65105
4.5106
17106
Conclusion
The offered inflatable electrostatic AB mast has gigantic advantages in comparison with
conventional space elevator. Main of them is follows: electrostatic mast can be built any
height without rockets, one needs material in tens times less them space elevator. That means
the electrostatic mast will be in hundreds times cheaper then conventional space elevator. One
can be built on the Earth‘s surface and their height can be increased as necessary. Their base
is very small.
The main innovations in this project are the application of electron gas for filling tube at
high altitude and a solution of a stability problem for tall (thin) inflatable mast by control
structure.
References
(Part of these articles the reader can find in author WEB page:
http://Bolonkin.narod.ru/p65.htm, http://arxiv.org , search "Bolonkin", and in the book
"Non-Rocket Space Launch and Flight", Elsevier, London, 2006,488 pgs.)
1. D.V. Smitherman, Jr., Space Elevators, NASA/CP-2000-210429.
2. K.E. Tsiolkovski:‖Speculations about Earth and Sky on Vesta,‖ Moscow, Izd-vo AN
SSSR, 1959; Grezi o zemle I nebe (in Russian), Academy of Sciences, U.S.S.R.,
Moscow, p.35, 1999.
3. A.C. Clarke: Fountains of Paradise, Harcourt Brace Jovanovich, New York, 1978.
4. Bolonkin, A.A., (1982), Installation for Open Electrostatic Field, Russian patent
application #3467270/21 116676, 9 July, 1982 (in Russian), Russian PTO.
5. Bolonkin, A.A., (1983), Method of stretching of thin film. Russian patent application
#3646689/10 138085, 28 September 1983 (in Russian), Russian PTO.
6. Bolonkin, A.A., (2002), ―Optimal Inflatable Space Towers of High Height‖.
COSPAR-02 C1.1-0035-02, 34th Scientific Assembly of the Committee on Space
Research (COSPAR), The World Space Congress – 2002, 10–19 Oct 2002,
Houston, Texas, USA.
7. Bolonkin, A.A., (2003), ―Optimal Inflatable Space Towers with 3-100 km Height‖,
JBIS, Vol. 56, No 3/4, pp. 87–97, 2003.
8. Bolonkin A.A.,(2004), ―Kinetic Space Towers and Launchers ‗, JBIS, Vol. 57, No
1/2, pp. 33–39, 2004.
9. Bolonkin A.A., (2006), Optimal Solid Space Tower, AIAA-2006-7717. ATIO
Conference, 25-27 Sept. 2006, Wichita, Kansas, USA. http://arxiv.org , search
"Bolonkin".
10. Bolonkin A.A., (2006) Non-Rocket Space Launch and Flight, Elsevier, 2006, 488 ps.
11. Book (2006),: Macro-Engineering - A challenge for the future. Collection of articles.
Eds. V. Badescu, R. Cathcart and R. Schuiling, Springer, (2006). (Collection contains
Bolonkin's articles: Space Towers; Cable Anti-Gravitator, Electrostatic Levitation
and Artificial Gravity).
12. Bolonkin A.A., Linear Electrostatic Engine, This work is presented as AIAA-2006-
206 Alexander Bolonkin
5229 for 42 Joint Propulsion Conference, Sacramento, USA, 9-12 July, 2006. Reader
finds it in http://arxiv.org , search "Bolonkin".
13. Bolonkin A.A., (2005), Problems of Electrostatic Levitation and Artificial Gravity,
AIAA-2005-4465. 41 Propulsion Conference, 10-12 July, 2005, Tucson, Arizona,
USA.
14. Bolonkin A.A., (2006c), Electrostatic AB-Ramjet Space Propulsion, AIAA/AAS
Astrodynamics Specialist Conference, 21-24 August 2006, USA. AIAA-2006-6173.
Journal "Aircraft Engineering and Aerospace Technology", Vol.79, #1, 2007.
http://arxiv.org , search "Bolonkin".
15. Bolonkin A.A., (2006), Articles, http://arxiv.org, search "Bolonkin".
16. Galasso F.S., Advanced Fibers and Composite, Gordon and Branch Science
Publisher, 1989.
17. Kikoin, I.K., (ed.), Tables of physical values. Atomuzdat, Moscow, 1976 (in
Russian).
18. Carbon and High Perform Fibers, Directory, 1995.
19. Dresselhous M.S., Carbon Nanotubes, Springer, 2000.
New Concepts, Ideas and Innovations in Aerospace… 207
Attachment Pictures for Part A, Ch. 11.
208 Alexander Bolonkin
Chapter 12
AB Levitrons and their Applications to Earth's
Motionless Satellites*
Abstract
Author offers the new and distinctly revolutionary method of levitation in artificial
magnetic field. It is shown that a very big space station and small satellites may be suspended
over the Earth's surface and used as motionless radio-TV translators, telecommunication
boosters, absolute geographic position locators, personal and mass entertainment and as
planet-observation platforms. Presented here is the theory of big AB artificial magnetic field
and levitation in it is generally developed. Computation of three macro-projects: space station
at altitude 100 km, TV-communication antenna at height 500 m, and multi-path magnetic
highway.
Key words: levitation, AB Levitrons, motionless space satellite.
* Presented as Bolonkin‘s paper to http://arxiv.org on Audust, 2007 (search ―Bolonkin‖).
Introduction
Brief history. The initial theory of levitation-flight was developed by the author during 1965
[1]. Theory of electrostatic levitation and artificial gravity for spaceships and asteroids was
presented as paper AIAA-2005-4465 in 41st Propulsion Conference, 10-13 July 2005, held in
Tucson, AZ, USA [2]. The related idea and theory extends from the author‘s work "Kinetic AntiGravitator"
[3] presented as paper AIAA-2005-4504 in 41st Propulsion Conference. The work
"AB Levitator and Electricity Storage" [4] was presented as paper AIAA-2007-4612 to 38th
AIAA Plasma dynamics and Lasers Conference in conjunction with the16th International
Conference on MHD Energy Conversion on 25-27 June 2007, Miami, USA. (See also
http://arxiv.org search "Bolonkin").
New Concepts, Ideas and Innovations in Aerospace… 209
The given work underwent further development and application of the above-cited works.
That allows an estimate of the parameters of low-altitude stationary satellites, space stations,
communication marts and cheap multi-path highway for levitation-flight trains and vehicles.
Innovations
The AB-Levitron uses two large conductivity rings with very high electric currency (fig.1).
They create intense magnetic fields. Directions of electric currency are opposed one to the other
and rings are repelling one from another. For obtaining enough force over a long distance, the
electric currency must be very strong. The current superconductive technology allows us to get
very high-density electric currency and enough artificial magnetic field in far space.
The superconductivity ring does not spend an electric energy and can work for a long time
period, but it requires an integral cooling system because the current superconductivity materials
have the critical temperature about 150-180 C (see Table #1).
However, the present computation methods of heat defense are well developed (for example,
by liquid nitrogen) and the induced expenses for cooling are small (fig.2).
The ring located in space does not need any conventional cooling—that defense from Sun
and Earth radiations is provided by high-reflectivity screens (fig.3). However, that must have parts
open to outer space for radiating of its heat and support the maintaining of low ambient
temperature. For variable direction of radiation, the mechanical screen defense system may be
complex. However, there are thin layers of liquid crystals that permit the automatic control of their
energy reflectivity and transparency and the useful application of such liquid crystals making it
easier for appropriate space cooling system. This effect is used by new man-made glasses which
grow dark in bright solar light.
210 Alexander Bolonkin
Figure 1. Explanation of AB-Levitron. (a) Artificial magnetic field; (b) AB-Levitron from two same closed
superconductivity rings; (c) AB-Levitron - motionless satellite, space station or communication mast.
Notation: 1- ground superconductivity ring; 2 - levitating ring; 3 - suspended stationary satellite
(space station, communication equipment, etc.); 4 - suspension cable; 5 - elevator (climber) and
electric cable; 6 - elevator cabin; 7 - magnetic lines of ground ring; R - radius of lover (ground)
superconductivity ring; r - radius of top ring; h - altitude of top ring; H - magnetic intensity; S - ring
area.
Figure 2. Cross-section of superconductivity ring. Notations: 1 - strong tube (internal part used for cooling
of ring, external part is used for superconductive layer); 2 - superconductivity layer; 3 - vacuum; 4 –
heat impact reduction high-reflectivity screens (roll of thin bright aluminum foil); 5 - protection and
heat insulation.
New Concepts, Ideas and Innovations in Aerospace… 211
Figure 3. Methods of cooling (protection from Sun radiation) the superconductivity levitron ring in outer
space. (a) Protection the ring by the super-reflectivity mirror [5]. (b) Protection by high-reflectivity
screen (mirror) from impinging solar and planetary radiations. (c) Protection by usual multi-screens.
Notations: 1 - superconductive wires (ring); 2 - heat protector (super-reflectivity mirror in Fig.3a and
a usual mirror in Fig. 3c); 2, 3 – high-reflectivity mirrors (Fig. 3b); 4 - Sun; 5 -Sun radiation, 6 - Earth
(planet); 7 - Earth's radiation.
The most inportant problem of AB-levitron is stability of top ring. The top ring is in
equilibrum, but it is out of balance when it is not parallel to the ground ring. Author offers to
suspend a load (satellite, space station, equipment, etc) lower then ring plate. In this case, a center
of gravity is lower a summary lift force and system become stable.
For mobile vehicles (fig.7) the AB-Levitron can have a run-wave of magnetic intensity
which can move the vehicle (produce electric currency), making it signicantly mobile in the
traveling medium.
Theory of AB-Levitron Estimations and Computations
1. Magnetic intensity. Exactly computation of the magnetic intencity and lift force is complex.
We find a simple formula only in two cases: (1) when top ring is small in comparison with
ground ring (r << . fig.1c) and located along ground ring axis and (2) the rings are same and
closed (h << R, fig.1b).
Results (case 1) are below
2 2 3/ 2
2
0
2 2 3/ 2
2
1/ 2 2 2
3
2
3
2( )
,
2( )
, .
2 2
R h
JR B
R h
JR H
R h
JS JR H
n
, (1)
where H is magnetic intensity, A/m, along an axis of the ground ring (fig.1a); J is electric
currency in the ground ring, A; S is ring area, m2
(fig.1a); is distance from ring element to
given point in ring axis, m (fig.1a); R is radius of ground ring, m; h is altitude of top ring, m;
o = 410-7
is magnetic constant, Bn is magnetic intensity which is perpendilar on top ring
plate in T.
2. Lift force. The lift force is
2 2 5/ 2
2 2
2 0
2( )
3
, ,
R h
iJr R h
p ir F
h
B
F p m
n
m
, (2)
where F is lift force, N; pm is magnetic moment of top ring, A/m2
; i is electric currency in
top ring, A; r is radius of top ring, m. The sing + or - depends from direction of electric
cirrency in top ring.
3. Optimal radius of ground ring for given altitude h. Lift force for given i, J, r, h has maximum
212 Alexander Bolonkin
,
0.186 0.8165 ,
3
2
, 0,
( )
2
2 2 5 / 2
2
h
R h h A
R
A
R h
R h
A
opt opt
(3)
Computation A is presented in fig.4.
Figure 4. Function A versus radius of the ground ring for altitude h = 60, 80, 100 km.
Note: For altitude h = 100 km, the optimal radius is Ropt = 81.65 km. However, the
decreasing this radius from 81.65 to 65 km decreases the lift force only in 5% (fig.4).
The magnetic intensity and force corresponding the Ropt are
r
h
h
h
iJ F
h
J
Bn R opt
R opt
, where
10
,
11.86 2
0 0
,
, (4)
Example: If i =107 A, J = 109 A,
h
=10, then F = 4106 N = 400 tons. If the h = 100 km that
means the R = 65 81 km, r = 10 km.
Computation of lift force for Ropt and relative altitude
h
=10 is presented in fig.5.
4. The lift force in case (2) (fig.1b). In this case the lift force is
h
R
F i J 0
, (5)
6. The lift force in case of linear AB-highway (fig. 7). This lift force can be estimated by
equation (h << L)
New Concepts, Ideas and Innovations in Aerospace… 213
h
iJ
h
L m F i J
h
L
F i J
7
0 1 0
2 10
2
1
, for 1 ,
2
, (6)
where L is length of AB-train (vehicle), m; F1 is lift force the 1 m length of train (vehicle).
The computation is presented in fig. 6.
Figure 5. Lift force of AB-Levitron space station versus the relative altitude for a product of the electric
currencies the superconductivity ground and station rings and for the optimal ground ring.
h =h/r, h is
station altitude, r is radius of top ring.
7. Lift force in general case. This lift force of the top ring can be computed by equation
z
B
p
y
B
p
x
B
x F p
F p grad B
x
m z
x
m y
x
x m x
m
or for axis
( )
. (7)
where pm = iSt
is magnetic moment, N.m; St
is area of top ring, m2
.
8. Some other parameters. The moment of force in the top ring is
M p B m
. (8)
When the currency in ground ring is variable, the voltage and electric currency in top ring are
t n
t
S B
r
E
i
dt
d
, , where , (9)
where E is voltage induced in top ring, V; is magnetic flow throw the top ring, Wb; rt
is
electric resistance of the top ring, .
The minimal radius RT,min [m] of the ring tube and a maximal magnetic pressure PT,max [N/m2
]
are
214 Alexander Bolonkin
2 2
2
0
0
2
,max
0
,min 8
,
2
,
2 T
T T T
R
i
P
B
P
B
i
R
, (10)
where B is maximum safety magnetic intensity for given superconductivity material, T (see
Table #1).
Example: for i = 107 A, B = 100 T we have RT,min = 5 mm, PT,max = 4109 N/m2
= 4104
atm.
The pressure is high. Steel 40X has a limit 4109 N/m2
, corundum has a limit 21109 N/m2
.
However, we can adopt a larger tube radius RT and, as a result, then decrease the magnetic
pressure. The internal cooling gas also has pressure which is opposed the magnetic pressure.
Figure 6. Lift force [N/m] of the 1 meter AB-Levitron multipath highway versus the train (vehicle) altitude
for a product (i1×i2
) of the electric currencies of the superconductivity ground and vehicle rings.
9. Energy of superconductivity ring, If the magnetic intensity into ring is constant, we can
estimate the energy needed for starting of ring:
2
0
2
0 0 0
0.25
2
,
2 2
,
2
, Φ
2
RI L I
E
R
R
S
S IL L
R
I
R
I
H
, (11)
where is magnetic flux, Wb: L is ring inductance, Henry; S is ring area, m2
; final equation in
(11) E is energy, J; I is electric currency, A.
Example: For ground ring having R = 10 km and I = 108 A the E = 1014 J = 2.51000 tons of fuel
(gas having specific energy 40106
J/kg). For top ring having R = 100 m and I = 106 A the E =
108
J = 2.5 kg of fuel (gas).
As the reader will undoubtedly readily note, the superconductivity ground ring is an excellent
storage of electric energy.
New Concepts, Ideas and Innovations in Aerospace… 215
10. Ring internal pressure is
2
2
0
2
0
8
,
2
,
2 r
i
f
r
i
H
H
f
r r
, (12)
In our macro-projects (for large r) this pressure is small.
11. Mass of suspension cables ms when ms << MS , ms << Mr
sin 2
2gr
ms
MS
, (13)
where MS is space station mass, kg; Mr
is top ring mass, kg; g = 9.81 m/s2
is gravity; is
specific mass of suspended cable, kg/m3
; is safety tensile stress of suspended cable, N/m2
; is
angle between plate of top ring and the suspended cable.
12. Minimal rotation speed of top ring for keeping of space station (when Mr >> ms)
V
r
t
M
grM V
r
S
2
,
sin 2
2
(14)
where V is rotation speed of top ring, m/s; t is time of one revolution, sec.
13. Superconductivity materials.
There are hundreds of new superconductivity materials (type2) having critical temperature
70 120 K and more.
Some of the superconductable materials are presented in Part A, Ch.1, Table 1 (2001). The
widely used YBa2Cu3O7 has mass density 7 g/cm3
.
The last decisions are: Critical temperature is 176 K, up 183 K. Nanotube has critical
temperature 12 - 15 K,
Some organic matters have a temperature of up to 15 K. Polypropylene, for example, is
normally an insulator. In 1985, however, researchers at the Russian Academy of Sciences
discovered that as an oxidized thin-film, polypropylene have a conductivity 105
to 106
that is
higher than the best refined metals.
Boiling temperature of liquid nitrogen is 77.3 K, air 81 K, oxygen 90.2 K, hydrogen 20.4 K,
helium 4.2 K [8].
Unfortutately, most superconductive material is not strong and needs a strong covering.
14. Computation of the cooling system. The following equations allow direct compution of the
proposed macro-project cooling systems.
3)Equation of heat balance of a body in vacuum
2
4
1
100
s
T
qs CS a
, (15)
where =1 is absorption coefficient of outer radiation, is reflection coefficient; q is heat
flow, W/m2
(from Sun at Earth's orbit q = 1400 W/m2
, from Earth q 440 W/m2
); s1 is area
under outer radiation, m2
; Cs = 5.67 W/m2K is heat coefficient; a 0.02 0.98 is blackness
coefficient; T is body temperature, K; s2 is area of body or screen, m2
.
2) Radiation heat flow q [W/m2
] between two parallel screens
216 Alexander Bolonkin
1/ 1/ 1
1
, ,
100 100 1 2
4
2
4
1
a Ca aCS a
T T
q C , (16)
where the lower index 1, 2 shows (at T and ) the number of screens; Ca is coerced coefficient of
heat transfer between two screens. For bright aluminum foil = 0.04 0.06. For foil covered
by thin bright layer of silver = 0.02 0.03.
When we use a vacuum and row (n) of the thin screens, the heat flow is
q
C
C
n
q
a
a
n
'
1
1
, (17)
where qn is heat flow to protected wire, W/m2
;
'
Ca
is coerced coefficient of heat transfer
between wire and the nearest screen, Ca is coerced coefficient of heat transfer between two
near by screens; n is number of screen (revolutins of vacuumed thin foil around central
superconductive wire).
Example: for
Ca
Ca
'
, n = 100, = 0.05, T1 = 298 K (15 C, everage Earth temperature), T2
= 77.3 K (liquid nitrogen) we have the qn = 0.114 W/m2
.
Expence of cooling liquid and power for converting back the vapor into cooling liquid are
ma
qn
/ , P qnS / , (18)
where ma is vapor mass of cooling liquid, kg/m2
.sec; P is power, W/m2
; S is an outer area of
the heat protection, m2
; is coefficient of efficiency the cooling instellation which convert
back the cooling vapor to the cooling liquid; is heat varoparation, J/kg (see Ch.1 A, Table
3).
3) When we use the conventional heat protection, the heat flow is computed by equations
q k(T1 T2
), k , (19)
where k is heat transmission coefficient, W/m2K; - heat conductivity coefficient, W/m.K. For
air = 0.0244, for glass-wool = 0.037; - thickness of heat protection, m.
The vacuum screenning is strong efficiency and light (mass) then the conventional cooling
protection.
These data are sufficient for a quick computation of the cooling systems characteristics.
Using the correct design of multi-screens, high-reflectivity solar and planetary energy
screen, and assuming a hard outer space vacuum between screens, we get a very small heat
flow and a very small expenditure for refrigerant (some gram/m2
per day in Earth). In outer
space the protected body can have low temperature without special liquid cooling system
(Fig.3).
For example, the space body (Fig. 3a) with innovative prism reflector [5] Ch. 3A ( = 106
, a
= 0.9) will have temperature 13 K in outer space. The protection Fig.3b gives more low
temperature. The usual multi-screen protection of Fig. 3c gives the temperature: the first
screen - 160 K, the second - 75 K, the third - 35 K, the fourth - 16 K.
15. Cable material. Let us consider the following experimental and industrial fibers,
whiskers, and nanotubes:
New Concepts, Ideas and Innovations in Aerospace… 217
5. Experimental nanotubes CNT (carbon nanotubes) have a tensile strength of 200 GigaPascals
(20,000 kg/mm2
). Theoretical limit of nanotubes is 30,000 kg/mm2
.
6. Young‘s modulus exceeds a Tera Pascal, specific density =1800 kg/m3
(1.8 g/cc) (year
2000).
For safety factor n = 2.4, = 8300 kg/mm2 = 8.3×1010 N/m2
, =1800 kg/m3
, (/)=46×106
.
The SWNTs nanotubes have a density of 0.8 g/cm3
, and MWNTs have a density of 1.8 g/cm3
(average 1.34 g/cm3
). Unfortunately, even in 2007 AD, nanotubes are very expensive to
manufacture.
7. For whiskers CD = 8000 kg/mm2
, = 3500 kg/m3
(1989) [5, p. 33]. Cost about $400/kg
(2001).
8. For industrial fibers = 500 – 600 kg/mm2
, = 1800 kg/m3
, = 2,78×106
. Cost about 2 -
5 $/kg (2003).
Relevant statistics for some other experimental whiskers and industrial fibers are given in
Table 2. Ch.1 A. See also Reference [5] p. 33.
16. Safety of space station.For safety of space station and elevator cabin the special parachutes
are utilized (see [9]). Author also has ideas for the safety of the ground supercondutivity ring.
Projects
Macro-Project #1. Stationary space station at altitude 100 km.
Let us to estimate the stationary space station is located at altitude h = 100 km. Take the
initial data: Electric currency in the top superconductivity ring is i = 106 A; radius of the top ring is
r = 10 km; electric currency in the superconductivity ground ring is J = 108 A; density of electric
currency is j = 106 A/mm2
; specific mass of wire is = 7000 kg/m3
; specific mass of suspending
cable and lift (elevator) cable is = 1800 kg/m3
; safety tensile stress suspending and lift cable is
= 1.5109 N/m2 = 150 kg /mm2
; = 45o
, safety superconductivity magnetic intensity is B = 100 T.
Mass of lift (elevator) cabin is 1000 kg.
Then the optimal radius of the ground ring is R = 81.6 km (Eq, (3), we can take R = 65 km);
the mass of space station is MS = F =40 tons (Eq.(2)). The top ring wire mass is 440 kg or
together with control screen film is Mr = 600 kg. Mass of two-cable elevator is 3600 kg; mass of
suspending cable is less 9600 kg, mass of parachute is 2200 kg. As the result the useful mass of
space station is Mu = 40 - (0.6+1+3.6+9.6+2.2) = 23 tons.
Minimal wire radius of top ring is RT = 2 mm (Eq. (10)). If we take it RT = 4 mm the
magnetic pressure will me PT =100 kg/mm2
(Eq. (10)). Minimal wire radius of the ground ring is
RT = 0.2 m (Eq. (10)). If we take it RT = 0.4 m the magnetic pressure will me PT =100 kg/mm2
(Eq.
(10)). Minimal rotation speed (take into consideration the suspending cable) is V = 645 m/s, time
of one revolution is t = 50 sec. Electric energy in the top ring is small, but in the ground ring is
very high E = 1014 J (Eq. (11)). That is energy of 2500 tons of liquid fuel (such as natural gas,
methane).
The requisite power of the cooling system for ground ring is about P = 30 kW (Eq. (18)).
As the reader observes, all parameters are accessible using existing and available
technology. They are not optimal.
Macro-Project #2. 500 m-high Tele-Communication Mast.
218 Alexander Bolonkin
Let us estimate the tele-communication mast of height h = 500 m without superconductivity
in the top ring. Take the initial data: Electric currency in the top ring is i = 100 A; radius of the top
ring is r = 200 m; electric currency in the superconductivity ground ring is J = 2.5108 A; density
of ground ring electric currency is j = 106 A/mm2
, the top ring has j = 5 A/mm2
; specific mass of
superconductivity wire is = 7000 kg/m3
; specific mass of aluminum wire is = 2800 kg/m3
;
specific mass of suspending cable and lift cable is = 1800 kg/m3
; safety tensile stress suspending
and list cable is = 10
9 N/m2 = 100 kg /mm2
; = 45o
, safety superconductivity magnetic
intensity is B = 100 T. The vertical wire transfer of electric energy has voltage 2000 V and electric
density 8.8 A/mm2
. Then the optimal radius of the ground ring is R = 400 m (Eq. (3)); the mass
of antenna is MS = F = 160 kg (Eq.(2)). The top ring wire mass is Mr = 70 kg. Mass of vertical
two-cable transfer of electric energy is 3 kg; mass of suspending cable is less 1 kg. As the result
the useful mass of top apparatuses is Mu = 160 - (70+3+1) = 86 kg.
Minimal wire radius of ground ring is RT = 0.5 m (Eq. (10)). If we take it RT = 1.5 m the
magnetic pressure will me PT = 44 kg/mm2
(Eq. (10)). Minimal rotation speed of top ring is V = 96
m/s, time of one revolution is t = 12.6 sec. Electric energy in the top ring is small, but in the
ground ring is high E = 2.51013 J (Eq. (11)). That is energy of 620 tons of liquid fuel (natural
gas). Requested energy for permanent supporting the electric currency in NONSUPERCONDUCTIVITY
top ring is 17.6 kW. If we make it superconductive, the lift force
increases by thousands times. For example, if i = 106 A the lift force increases in 106
/100 = 104
times and became 1.6103 tons. That is suspending mobile building (hotel). There is no expense of
electric energy for superconductivity ring. The power for cooling (liquid nitrogen) is small. It is
not used an expensive city area.
As it is shown in the author work [4] we can build the fight city where men can fly as
individuals and also in the cars or similar vehicles.
All parameters are accessible for existing industry. They are not optimal. Our aim - it shows
that AB-Levitron may be designed by the current technology (see also [11]).
Macro-Project #3. Levitron AB-miltipath highway.
The AB-levitron may be used for design the multi-path levitation highway (fig.7). That is
the closed-loop superconductive lenthy linear strung near the highway which creates the vertical
magnetic field. The lift force produced by this AB-highway in one meter of length is [Eq. (6)]
h
i i
F
1 2
7
1
2 10
, (17)
where F1 is lift force, N/m; i is electric currency in graund cable and fly train (vehicle)
respectively; h is altitude of the veficle (train) over graund cable, m.
Estimations. Let us take the electric currency i1 = 108 A in ground line. Then:
1) If the the train does not have the superconductivity wire, the electric currency in top ring
is only i2 = 100 A and distance between rings is h = 0.5 m, the lift force of 1 m train
length will be F1 = 4000 N/m (Eq. (6 or 17)). In this case the top ring may be changed by
permanent magnets.
2) If the vehicle has the supercondutivity with currency i2 = 106 A then the 1 m length of
vehicle will has:
a) at altitude h = 10 m the F1 = 200 ton/m ;
b) at altitude h = 100 m the F1 = 20 ton/m ;
c) at altitude h = 1000 m the F1 = 2 ton/m ;
New Concepts, Ideas and Innovations in Aerospace… 219
If vertical distance between paths is 10 meter the 1 km vertical corridor will have 100 ways
in one direction from a lower low speed vehicles to a top high speed vehicles (supersonic aircraft).
They can receive energy from running magnet wave of graund cable.
Figure 7. High speed AB-Levitron way for levitating aircraft or trains. Notations: 1 - ground
superconductivity closed-loop cable; 2 - car, track, air vehicle or train.
The offered AB-Llevitron vehicle has following advantages in comparison the current train
used magnet pillow (maglev):
1) One does not need in complex expencive magnet system;
2) That does not need a precise concrete roadbed;
3) There area a lot of ways and train can change a path and it does not depend from
condition of other train and vehicles,
The initial data in all our macro-projects are not optimal.
Figure 8. Possible levitron.
Discussion
The offered AB-Levitrons may be made with only existing technology. We have a
superconductivity material (see Table 1), the strong artificial fibers and whiskers (Table 3), the
light protection and cooling system (Table 2) for the Earth's surface, and the radiation screens for
outer space. The Earth has weak magnetic field, the Sun and many planets and their satellites (as
Phobos orbiting Mars) has also small magnetic field. There is no barrier problem to creating the
artificial magnetic field on Earth, asteroids and planetary satellites (for example, to create local
artificial magnetic field on the Moon, see [10]). We have a very good perspective in improving our
220 Alexander Bolonkin
devices because—especially during the last 30 years—the critical temperature of the
superconductive material increases from 4 K to 186 K and does not appear, at this time, to be any
theoretical limit for further increase. Moreover, Russian scientists received the thin layers which
have electric resistance at room temperature in many times less than the conventinal conductors.
We have nanotubes which will create the jump in AB-Levitrons, when their production will be
cheaper. The current superconductive solenoids have the magnetic field B 20 T.
AB-levitrons can instigate a revolution in space exploration and exploitation, telecommunication
and air, ground, and space vehicle transportation. They allow individuals to fly as
birds, almost flight with subsonic and supersonic speed [4]. The AB-Levitrons solve the
environment problem because they do not emit or evolve any polluting gases. They are useful in
any solution for the national and international oil-dependence problem because they use electricity
and spend the energy for flight and other vehicles (cars) many times less than conventional
internal combustion engine (no graund friction). In difference of a ground car, the levitation car
flights are straight line to objective in a city region.
The AB-Levitrons create a notable revolution in tele-communication by the low-altitude
stationary suspended satellites, in energy industry, and especially in a local aviation. They are
very useful in night-lighting of Earth-biosphere regions by additional light and heat Sun radiation
because, in difference from conventional mobile space mirrors, they can be suspended over given
place (city) and service this place efficiently.
It is interesting, the toroidal AB engine is very comfortable for flying discs (human-made
UFO!) and have same property with UFOs. That can levitate and move in any direction with high
acceleration without turning of vehicle, that does not excrete any gas, jet, and that does not
produce a noise [4].
Conclusion
We must research and develop these ideas. They may accelerate the technical progress and
improve our life-styles. There are no known scientific obstacles in the development and design of
the AB-Levitrons, levitation vehicles, high-speed aircraft, spaceship launches, low-aititude
stationary tele-communication satellites, cheap space trip to Moon and Mars and other interesting
destination-places in outer space.
References
(see some Bolonkin's articles in Internet: http://Bolonkin.narod.ru/p65.htm , and
http://arxiv.org search "Bolonkin")
1. Bolonkin A.A., "Theory of Flight Vehicles with Control Radial Force", Collection
Researches of Flight Dynamics, Mashinostroenie Publisher, Moscow, 1965, pp. 79 - 118,
(in Russian). International Aerospace Abstract A66-23338# (in English).
2. Bolonkin A.A., Electrostatic Levitation and Artificial Gravity, presented as paper AIAA2005-4465,
41st Propulsion Conference, 10-13 July 2005, Tucson, AZ, USA.
3. Bolonkin A.A., Kinetic Anti-Gravitator, Presented as paper AIAA-2005-4504, 41st
Propulsion Conference, 10-13 July 2005, Tucson, AZ, USA.
4. Bolonkin A.A., "AB Levitator and Electricity Storage", presented as paper AIAA-2007-
4612 to 38th AIAA Plasmadynamics and Lasers Conference in conjunction with the16th
International Conference on MHD Energy Conversion on 25-27 June 2007, Miami, USA.
http://arxiv.org search "Bolonkin".
5. Bolonkin A.A., Non-Rocket Space Launch and Flight, Elsevier, London, 2006, 488 pgs.
6. Bolonkin A.A., Electrostatic Space Towers and Masts. See http://arxiv.org search
"Bolonkin".
7. AIP, Physics Desk Reference, 3-rd Ed. Springer, 2003.
8. Koshkin N.I. Reference book of elementary physics, Nauka, Moscow, 1982 (Russian).
New Concepts, Ideas and Innovations in Aerospace… 221
9. Bolonkin A.A., New Method Re-entry space ships, http://arxiv.org search "Bolonkin".
10. Bolonkin A.A., Inflatable Dome for Moon, Mars, Asteroids and Satellites. Presented as
paper AIAA-2007-6262 by AIAA Conference "Space-2007", 18-20 September 2007,
Long Beach. CA, USA. See http://arxiv.org search "Bolonkin".
222 Alexander Bolonkin
PART B. NEW IDEAS IN TECHNOLOGY
Chapter 1
MICRO (MINI) –THERMONUCLEAR
AB-REACTORS
ABSTRACT
About fifty years ago, scientists conducted Research and Development of a
thermonuclear reactor that promises a true revolution in the energy industry and,
especially, in aerospace. Using such a reactor, aircraft could undertake flights of very
long distance and for extended periods and that, of course, decreases a significant cost of
aerial transportation, allowing the saving of ever-more expensive imported oil-based
fuels. (As of mid-2006, the USA DoD has a program to make aircraft fuel from domestic
natural gas sources.) The temperature and pressure required for any particular fuel to fuse
is known as the Lawson criterion L. Lawson criterion relates to plasma production
temperature, plasma density and time. The thermonuclear reaction is realised when L is
more certain magnitude. There are two main methods of nuclear fusion: inertial
confinement fusion (ICF) and magnetic confinement fusion (MCF). Existing
thermonuclear reactors are very complex, expensive, large, and heavy. They cannot
achieve the Lawson criterion.
The author offers several innovations that he first suggested publicly early in 1983
for the AB multi-reflex engine, space propulsion, getting energy from plasma, etc. (see:
A. Bolonkin, Non-Rocket Space Launch and Flight, Elsevier, London, 2006, Chapters 12,
3A). It is the micro-thermonuclear AB-Reactors. That is new micro-thermonuclear
reactor with very small fuel pellet that uses plasma confinement generated by multireflection
of laser beam or its own magnetic field. The Lawson criterion increases by
hundreds of times. The author also suggests a new method of heating the power-making
fuel pellet by outer electric current as well as new direct method of transformation of ion
kinetic energy into harvestable electricity. These offered innovations dramatically
decrease the size, weight and cost of thermonuclear reactor, installation, propulsion
system and electric generator. Non-industrial countries can produce these researches and
constructions. Currently, the author is researching the efficiency of these innovations for
two types of the micro-thermonuclear reactors: multi-reflection reactor (ICF) and selfmagnetic
reactor (MCF).
Keywords: Micro-thermonuclear reactor, Multi-reflex AB-thermonuclear reactor, Selfmagnetic
AB-thermonuclear reactor, aerospace thermonuclear engine.
Presented as Bolonkin‘s paper AIAA-2006-8104 in 14th Space Plane and Hypersonic Systems Conference, 6-8
November, 2006, USA.
New Concepts, Ideas and Innovations in Aerospace… 223
INTRODUCTION
Brief Information about Thermonuclear Reactors
Fusion power is useful energy generated by nuclear fusion reactions. In this kind of
reaction two light atomic nuclei fuse together to form a heavier nucleus and release energy.
The largest current experiment, JET, has resulted in fusion power production somewhat larger
than the power put into the plasma, maintained for a few seconds. In June 2005, the
construction of the experimental reactor ITER, designed to produce several times more fusion
power than the power into the plasma over many minutes, was announced. The production of
net electrical power from fusion is planned for the next generation experiment after ITER.
Unfortunately, this task is not easy, as scientists thought early. Fusion reactions require a
very large amount of energy to initiate in order to overcome the so-called Coulomb barrier or
fusion barrier energy. The key to practical fusion power is to select a fuel that requires the
minimum amount of energy to start, that is, the lowest barrier energy. The best fuel from this
standpoint is a one-to-one mix of deuterium and tritium; both are heavy isotopes of hydrogen.
The D-T (Deuterium and Tritium) mix has a low barrier energy. In order to create the
required conditions, the fuel must be heated to tens of millions of degrees, and/or compressed
to immense pressures.
At present, D-T is used by two main methods of fusion: inertial confinement fusion (ICF)
and magnetic confinement fusion (MCF)(for example, tokamak).
In inertial confinement fusion (ICF), nuclear fusion reactions are initiated by heating and
compressing a target. The target is a pellet that most often contains deuterium and tritium
(often only micro or milligrams). Intense laser or ion beams are used for compression. The
beams explosively detonate the outer layers of the target. That accelerats the underlying target
layers inward, sending a shockwave into the center of pellet mass. If the shockwave is
powerful enough and if high enough density at the center is achieved some of the fuel will be
heated enough to cause fusion reactions. In a target which has been heated and compressed to
the point of thermonuclear ignition, energy can then heat surrounding fuel to cause it to fuse
as well, potentially releasing tremendous amounts of energy.
Fusion reactions require a very large amount of energy to initiate in order to overcome
the so-called Coulomb barrier or fusion barrier energy.
Magnetic confinement fusion (MCF). Since plasmas are very good electrical conductors,
magnetic fields can also confine fusion fuel. A variety of magnetic configurations can be
used, the basic distinction being between magnetic mirror confinement and toroidal
confinement, especially tokamaks and stellarators.
Lawson criterion. In nuclear fusion research, the Lawson criterion, first derived by John
D. Lawson in 1957, is an important general measure of a system that defines the conditions
needed for a fusion reactor to reach ignition, that is, that the heating of the plasma by the
products of the fusion reactions is sufficient to maintain the temperature of the plasma against
all losses without external power input. As originally formulated the Lawson criterion gives a
minimum required value for the product of the plasma (electron) density ne and the "energy
confinement time" τ. Later analyses suggested that a more useful figure of merit is the "triple
product" of density, confinement time, and plasma temperature T. The triple product also has
a minimum required value, and the name "Lawson criterion" often refers to this inequality.
224 Alexander Bolonkin
The key to practical fusion power is to select a fuel that requires the minimum amount of
energy to start, that is, the lowest barrier energy. The best fuel from this standpoint is a oneto-one
mix of deuterium and tritium; both are heavy isotopes of hydrogen. The D-T
(Deuterium and Tritium) mix has a low barrier.
In order to create the required conditions, the fuel must be heated to tens of millions of
degrees, and/or compressed to immense pressures. The temperature and pressure required for
any particular fuel to fuse is known as the Lawson criterion. For the D-T reaction, the
physical value is about
or (10 10 ) in CI units
(10 10 ) in "cgs" units
20 21
14 15
L nT
L ne
T
,
where T is temperature, [KeV], 1 eV = 1.16104 oK; ne
is matter density, [1/сm
3
]; n is matter
density, [1/m3
]; is time, [s]. Last equation is in metric system. The thermonucler rection of
2H + 3D realises if L > 1020 in CI (meter, kilogram, second) units or L > 1014 in 'cgs'
(cantimetr, gram, second) units.
This number has not yet been achieved in any reactor, although the latest generations of
machines have come close. For instance, the reactor TFTR has achieved the densities and
energy lifetimes needed to achieve Lawson at the temperatures it can create, but it cannot
create those temperatures at the same time. Future ITER aims to do both.
The Lawson criterion applies to inertial confinement fusion as well as to magnetic
confinement fusion but is more usefully expressed in a different form. Whereas the energy
confinement time in a magnetic system is very difficult to predict or even to establish
empirically, in an inertial system it must be on the order of the time it takes sound waves to
travel across the plasma:
mi
kT
R
/
where is time, s; R is distance, m; k is Boltzmann constant; mi
is mass of ion, kg.
Following the above derivation of the limit on neτE, we see that the product of the density
and the radius must be greater than a value related to the minimum of T
3/2/<σv> (here is
Boltzmann constant, v is ion speed). This condition is traditionally expressed in terms of the
mass density ρ: ρR > 1 g/cm² .
To satisfy this criterion at the density of solid D+T (0.2 g/cm³) would require an
implausibly large laser pulse energy. Assuming the energy required scales with the mass of
the fusion plasma (Elaser ~ ρR3
~ ρ
-2
), compressing the fuel to 103
or 104
times solid density
would reduce the energy required by a factor of 106
or 108
, bringing it into a realistic range.
With a compression by 103
, the compressed density will be 200 g/cm³, and the compressed
radius can be as small as 0.05 mm. The radius of the fuel before compression would be 0.5
mm. The initial pellet will be perhaps twice as large since most of the mass will be ablated
during the compression.
The fusion power density is a good figure of merit to determine the optimum temperature
for magnetic confinement, but for inertial confinement the fractional burn-up of the fuel is
probably more useful. The burn-up should be proportional to the specific reaction rate
New Concepts, Ideas and Innovations in Aerospace… 225
(n²<σv>) times the confinement time (which scales as T
1/2) divided by the particle density n:
burn-up fraction ~ n²<σv> T
-1/2 / n ~ (nT) (<σv>/T
3/2)
Thus the optimum temperature for inertial confinement fusion is that which maximizes
<σv>/T
3/2, which is slightly higher than the optimum temperature for magnetic confinement.
Short history of thermonuclear fusion. One of the earliest (in the late 1970's and early
1980's) serious attempts at an ICF design was Shiva, a 20-armed neodymium laser system
built at the Lawrence Livermore National Laboratory (LLNL) that started operation in 1978.
Shiva was a "proof of concept" design, followed by the NOVA design with 10 times the
power. Funding for fusion research was severely constrained in the 80's, but NOVA
nevertheless successfully gathered enough information for a next generation machine whose
goal was ignition. Although net energy can be released even without ignition (the breakeven
point), ignition is considered necessary for a practical power system.
The resulting design, now known as the National Ignition Facility, commenced being
constructed at LLNL in 1997. Originally intended to start construction in the early 1990s, the
NIF is now six years behind schedule and overbudget by over $1.4 billion. Nevertheless
many of the problems appear to be due to the "big lab" mentality and shifting the focus from
pure ICF research to the nuclear stewardship program, LLNLs traditional nuclear weaponsmaking
role. NIF is now scheduled to "burn" in 2010, when the remaining lasers in the 192-
beam array are finally installed.
Laser physicists in Europe have put forward plans to build a £500m facility, called
HiPER, to study a new approach to laser fusion. A panel of scientists from seven European
Union countries believes that a "fast ignition" laser facility could make a significant
contribution to fusion research, as well as supporting experiments in other areas of physics.
The facility would be designed to achieve high energy gains, providing the critical
intermediate step between ignition and a demonstration reactor. It would consist of a longpulse
laser with an energy of 200 kJ to compress the fuel and a short-pulse laser with an
energy of 70 kJ to heat it.
Confinement refers to all the conditions necessary to keep a plasma dense and hot long
enough to undergo fusion:
• Equilibrium: There must be no net forces on any part of the plasma, otherwise it will
rapidly disassemble. The exception, of course, is inertial confinement, where the
relevant physics must occur faster than the disassembly time.
• Stability: The plasma must be so constructed that small deviations are restored to the
initial state, otherwise some unavoidable disturbance will occur and grow
exponentially until the plasma is destroyed.
• Transport: The loss of particles and heat in all channels must be sufficiently slow.
The word "confinement" is often used in the restricted sense of "energy
confinement".
To produce self-sustaining fusion, the energy released by the reaction (or at least a
fraction of it) must be used to heat new reactant nuclei and keep them hot long enough that
they also undergo fusion reactions. Retaining the heat generated is called energy confinement
and may be accomplished in a number of ways.
The hydrogen bomb weapon has no confinement at all. The fuel is simply allowed to fly
apart, but it takes a certain length of time to do this, and during this time fusion can occur.
This approach is called inertial confinement (Figure 1). If more than about a milligram of fuel
226 Alexander Bolonkin
is used, the explosion would destroy the machine, so controlled thermonuclear fusion using
inertial confinement causes tiny pellets of fuel to explode several times a second. To induce
the explosion, the pellet must be compressed to about 30 times solid density with energetic
beams. If the beams are focused directly on the pellet, it is called direct drive, which can in
principle be very efficient, but in practice it is difficult to obtain the needed uniformity. An
alternative approach is indirect drive, in which the beams heat a shell, and the shell radiates xrays,
which then implode the pellet. The beams are commonly laser beams, but heavy and
light ion beams and electron beams have all been investigated and tried to one degree or
another.
They rely on fuel pellets with a "perfect" shape in order to generate a symmetrical inward
shock wave to produce the high-density plasma, and in practice these have proven difficult to
produce. A recent development in the field of laser-induced ICF is the use of ultra-short pulse
multi-petawatt lasers to heat the plasma of an imploding pellet at exactly the moment of
greatest density after it is imploded conventionally using terawatt scale lasers. This research
will be carried out on the (currently being built) OMEGA EP petawatt and OMEGA lasers at
the University of Rochester and at the GEKKO XII laser at the Institute for Laser Engineering
in Osaka Japan which, if fruitful, may have the effect of greatly reducing the cost of a laser
fusion-based power source.
Figure 1. Laser installation for NOVA inertial thermonuclear reactor. Look your attention in the man
and gigantic size of laser installation for reactor. Cost is some billions of dollars.
At the temperatures required for fusion, the fuel is in the form of a plasma with very good
electrical conductivity. This opens the possibility to confine the fuel and the energy with
magnetic fields, an idea known as magnetic confinement (Figure 2).
Much of this progress has been achieved with a particular emphasis on tokamaks (Figure
2).
New Concepts, Ideas and Innovations in Aerospace… 227
Figure 2. Magnetic thermonuclear reactor. The size of the installation is obvious if you compare it with
the ―Little Blue Man‖ inside the machine at the bottom. Cost is some tens of billions of dollars.
In fusion research, achieving a fusion energy gain factor Q = 1 is called breakeven and is
considered a significant although somewhat artificial milestone. Ignition refers to an infinite
Q, that is, a self-sustaining plasma where the losses are made up for by fusion power without
any external input. In a practical fusion reactor, some external power will always be required
for things like current drive, refueling, profile control, and burn control. A value on the order
of Q = 20 will be required if the plant is to deliver much more energy than it uses internally.
In a fusion power plant, the nuclear island has a plasma chamber with an associated
vacuum system, surrounded by a plasma-facing components (first wall and divertor)
maintaining the vacuum boundary and absorbing the thermal radiation coming from the
plasma, surrounded in turn by a blanket where the neutrons are absorbed to breed tritium and
heat a working fluid that transfers the power to the balance of plant. If magnetic confinement
is used, a magnet system, using primarily cryogenic superconducting magnets, is needed, and
usually systems for heating and refueling the plasma and for driving current. In inertial
confinement, a driver (laser or accelerator) and a focusing system are needed, as well as a
means for forming and positioning the pellets.
The magnetic fusion energy (MFE) program seeks to establish the conditions to sustain a
nuclear fusion reaction in a plasma that is contained by magnetic fields to allow the
successful production of fusion power.
In thirty years, scientists have increased the Lawson criterion of the ICF and tokamak
installations by tens of times. Unfortunately, all current and some new installations (ICF and
totamak) have a Lawrence criterion that is tens of times lower than is necessary (Figure 3).
228 Alexander Bolonkin
Figure 3. Parameter space occupied by inertial fusion energy and magnetic fusion energy devices. The
regime allowing thermonuclear ignition with high gain lies near the upper right corner of the plot.
INNOVATION
As you can see in the Equation for thermonuclear reaction (reaction‘s "ignition") it is
necessary to rapidly and greatly increase the target-enveloping temperature, the density of
target proper and to shorten the time of the operation in order to keep the fuel in these
precisely induced conditions. In ICF the density of plasma is very high (1028
m
-3
, it increases
in 20-30 times in target), the temperature reaches tens of millions oK, but time is measured in
nanoseconds. As a result, the Lawson criterion is tens to hundreds of times lower than is
required. In a tokomak, the time is mere parts of second and the ambient temperature is tens
of millions of degrees, but density of plasma is very small (1020
m
-3
). The Lawson criterion is
also tens to hundreds of times lower than needed.
The author offers some innovations and names these reactors as AB-reactors.. The main
innovations are below.
Multi-reflect reactor (MRR). The first innovation suggested early in 1983 [14] and
developed later in [1]-[26] for multi-reflex engine and space propulsion. Conventional ICF
has conventional inside surface of the combustion chamber. This surface absorbs part of the
heat radiation emanating from the pellet and plasma, the rest of the radiation reflects in all
directions and is also absorbed by walls of combustion chamber. As result the target loses
energy expensively delivered by lasers. This loss is so huge that we need very powerful lasers
and we cannot efficiently heat the target to reach ignition temperature (Lawson‘s criterion). In
all current ICF installations this loss is tens of times more than is acceptable.
New Concepts, Ideas and Innovations in Aerospace… 229
The innovative ICF has, on the inside surface of combustion chamber, a covering of
small Prism Reflectors (PR) (figs. 4, 5) (or multi-layer reflector. Note: Multi-layer reflector
can only reflect the laser beam). The system of prism reflectors has great advantages in
comparison with conventional mirror and especially with conventional combustion chamber.
The advantages are listed:
(1) The prism reflector has very high efficiency. The coefficient of its radiate absorption
is less about million times the rate of the conventional mirror.
(2) The prism mirror reflects the radiation in widely diapason of continuous spectrum. A
conventional mirror reflects the radiation only in narrow diapason of continuous
spectrum. That means that any conventional mirror has big absorption of radiation
energy even if it has high reflectivity (up 99%) in narrow interval of the continuous
spectrum. The prism reflector allows to use the thermal plasma radiation.
(3) The prism reflector bounces the heat radiation exactly to a point where heat beam
comes up, even if it has defect at position. The conventional mirror having small
defect in position (or the pellet is not located exactly in center of sphere) destroys the
pellet.
(4) According with Point 3 above, the prism reflector may be used in cylindrical
(toroidal) camera (Figure5) (tokomak, stellarator). A conventional mirror cannot be
employed because reflected ray will be sent in the other direction.
(5) The prism reflector can uniformly distribute the beam energy in pellet surface. The
small spherical plasma pellet reflected the scattered radiation. That means the laser
beam after the first reflection reflects on semi-sphere, after two reflections that
presses on full sphere, after 3 - 4 reflection the pressure is almost uniformly. That
decreases a number of needed laser beams, simplify, and decreases cost of laser
installation.
In particular, this innovation may be used in already built current reactors for their
improvement.
Self-Magnetic reactor (SMR) (Figures 6, 7). The magnetic pressure is proportional to the
inverse value of electric conductor diameter. (The conventional magnetic reactor has a
diameter of plasma flex some meters). The high temperature plasma has excellent
conductivity which does not depend from plasma density. If the diameter is decreased to 0.1
mm and electric currency is high, the magnetic pressure is increased by hundreds or thousand
times and that can keep the high-density plasma. Thus, the plasma is confined by selfgenerated
magnetic field (and by pinch-effect) and it does not need in powerful outer
magnetic field created very complex, high cost super-conductivity system! This innovation in
MCF is dramatically decreasing the size of reaction zone and using of gaseous compression
fuel pellet (micro-capsule) in magnetic confinement reactor.
230 Alexander Bolonkin
Figure 4. Multi-reflex Reactor. (a) Cross-section of ICF; (b) Cross-section of spherical combustion
chamber and prism reflectors. Notations: 1 - spherical shell; 2 - target (pellet); 3- ignition laser beams; 4
- reflected laser beams; 5 - prism reflector.
Figure 5. Multi-reflective in cylindrical tube chamber or tokomak. (a) Cross-section along long axis.
(b) Cross-section along transverse axis; (c) Cross-section of toroidal or cylindrical combustion and
prism reflectors. Notations: 1 - combustion chamber; 2 - plasma (fuel capsule); 3 - reflected laser
beams; 5 - prism reflectors.
The other innovation in SMR is uses the electric current (electric impulse) for initial
heating of microcapsule targets. That means we don't need a large, very complex and
expensive laser (or ion beam) system for inertial confinement reactor or induce system in
magnetic confinement reactor. That is possible in special design of the fuel microcapsule. The
energy for heating of the microcapsule to thermonuclear temperature is small and
conventional condensers may be used for it.
New Concepts, Ideas and Innovations in Aerospace… 231
Figure 6. Micro AB-reactor with self-magnetic confinement and radiation support of plasma. (a) – fuel
micro-capsule and electrodes; (b) - Reflective camera. Notations: 1 - micro fuel capsule; 2 -
thermonuclear fuel into capsule; 3 - capsule shell and covering; 4 - electrodes; 5 - feeding of capsule; 6
- electric currency (electron injector); 7 - magnetic stopper; 8 - cooling system; 9 - thermo protection;
10 - radiation; 11 - additional radiation pressure to fuel capsule ends.
Figure 7. Micro AB-thermonuclear reactor with self-magnetic confinement. (a) Self-magnetic field
around fuel capsule, (b) - Explosion initial compression, (c) Magnetic intensity distribution in crosssection
plasma flex, (d) Fuel capsule. Notations: 4 - electrodes; 5 - feeding of capsule; 6 - electric
currency (electron injector); 7 - magnetic stopper; 8 - cooling system; 9 - thermo protection; 11 -
additional end capsule pressure of self-magnetic field and radiation; 12 - magnetic corks. 13 - selfmagnetic
field of capsule (and pinch-effect).
232 Alexander Bolonkin
The self-magnetic reactor uses very small capsule diameter when the magnetic intensity
is very high. The magnetic intensity has good distribution (decreases to plasma center, Figure
7c) and magnetic pressure is big (it is enough to keep the kinetic plasma pressure which is not
so much for low density plasma).
The some innovations are magnetic and radiation stoppers (confinements) of plasma in
ends of the fuel capsule. It is suggested two methods:
(1) The capsule has conic ends (Figure 7d). The capsule radius decreases at ends. That
means the magnetic intensity will increase at the capsule ends (up 10 and more
times). They will work as magnetic mirror (plasma stopper) (Figure 7).
(2) Our magnetic field has other direction and form then it is in conventional tokomak.
In tokomak the magnetic lines are parallel to a toroid (or cylinder) axis. In our SMR
the magnetic lines are circles around cylindrical capsule. That means there is an axis
magnetic force which put obstacles a heat transfer from plasma to electric electrodes.
That works as radial and axial magnetic stopper.
There are others innovations which reader can apprehend in comparison the offered
micro AB-reactors and current and under construction reactors.
These innovations decrease the size, weight and the monetary cost of thermonuclear
reactors by thousands of times and allow the widespread future construction of thermonuclear
electric stations, engines, and space propulsions.
The offered self-magnetic reactor has the following differences in comparison with Z -
machine of Sandia Laboratory (USA). Z-machine used a set of very fine tungsten wires
running around the fuel would be "dumped" with the current instead. The wires would
quickly vaporize into a plasma, which is conductive, and the current flow would then cause
the plasma to pinch. The key difference is that the plasma would not be the fuel, as in our
SMR, but used solely to generate very high-energy X-rays as the metal plasma compressed
and heated. The x-rays would compress a tiny fuel cylinder containing deuterium-tritium mix,
in the same fashion that the X-rays generated from a nuclear bomb compress the fuel load in
an H-bomb. The superpower x-ray output pulse (up 2.7 megajouls!) generated by heavy
tungsten metal plasma (
184
74W
) is very danger for people. In additional, the powerful
fluctuation in the magnetic field (an "electromagnetic pulse") also generates strong electric
current in all of the metallic objects in the room and demiges electronic devices. In our
machime the small fuel cylinder has a thin conductive layer from light metall. The capsule
can also have contactivity filaments into fuel. They help to produce initial heating of fuel
plasma (up 104
105 oK) and initial the plasma compression (rocket and/or inertial). The
father plasma heating and confinement is produced by voltage curve of Figure 17 which
create self-magnetic field equil (or more) plasma gas pressure.
Summary. This work offers two types of micro-AB-thermonuclear reactors: by multireflex
radiation confinement of plasma and self-magnetic confinement. They can use high and
low density fuel (compressed gas or liquid/frizzed fuel) and they can work in pulse or
continuous regimes.
The offered micro-AB-reactor with self-magnetic confinement includes: micro fuel
capsule with compressed gaseous or liquid (frizzed) fuel; two electric electrodes, and a
New Concepts, Ideas and Innovations in Aerospace… 233
combustion chamber. Internal surface of combustion chamber is covered by prism or multilayer
reflectors.
The capsule contains thermonuclear fuel (it conventionally has two component, example
D + T), and conducting capsule shell. Fuel may be composed by conducting fiber for quick
heating. The capsule has the conic ends.
The electric electrodes have windings for creating magnetic locks, canals for feeding of
fuel capsule (or injector for liquid fuel), and electron injector (electric currency). Last may be
electron (currency) emitter. Electrodes also contain a cooling system and thermo-protection.
The suggested reactor works the following way. The strong impulse electric current
passes through capsule. The capsule shell explodes, creating an initial plasma flux and
compressed, heating, and creating initial fuel plasma fuse. The plasma radiation erupts and
part of them returns and compresses the plasma, helping the electric current to heat the
plasma to its ignition temperature.
We spoke about micro AB-reactors. But it does not mean that power of them is small. In
next articles I will discuss the methods for transformation and utilization of the thermonuclear
energy into other types of energy and propulsion. These completed research show the power
of micro AB-reactor can reach some thousands of kW.
The computations of the offered reactors are presented below.
THEORY OF CURRENT THERMONUCLEAR REACTOR
Methods of Confinement in Current Reactors
Magnetic confinement. Magnetic fields can confine fusion fuel because plasma is a very
good electrical conductor. A variety of magnetic configurations can be used, the most basic
distinction being tokamaks and stellarators.
Inertial confinement. A third confinement principle is to apply a rapid pulse of energy to
a large part of the surface of a pellet of fusion fuel, causing it to simultaneously "implode"
and heat to very high pressure and temperature. If the fuel is dense enough and hot enough,
the fusion reaction rate will be high enough to burn a significant fraction of the fuel before it
has dissipated. To achieve these extreme conditions, the initially cold fuel must be
explosively compressed. Inertial confinement is used in the hydrogen bomb, where the driver
is x-rays created by a fission bomb. Inertial confinement is also attempted in "controlled"
nuclear fusion, where the driver is a laser, ion, or electron beam.
Some other confinement principles have been investigated, such as muon-catalyzed
fusion, the Farnsworth-Hirsch fusor (inertial electrostatic confinement), and bubble fusion.
In man-made fusion, the primary fuel is not constrained to be protons and higher
temperatures can be used, so reactions with larger cross-sections are chosen. This implies a
lower Lawson criterion, and therefore less startup effort. Another concern is the production of
neutrons, which activate the reactor structure radiologically, but also have the advantages of
allowing volumetric extraction of the fusion energy and tritium breeding. Reactions that
release no neutrons are referred to as aneutronic.
In order to be useful as a source of energy, a fusion reaction must satisfy several criteria.
It must:
234 Alexander Bolonkin
• be exothermic - This may be obvious, but it limits the reactants to the low Z (number
of protons) side of the curve of binding energy. It also makes helium 4He the most
common product because of its extraordinarily tight binding, although 3He and 3H
also show up.
• involve low Z nuclei - This is because the electrostatic repulsion must be overcome
before the nuclei are close enough to fuse.
• have two reactants - At anything less than stellar densities, three body collisions are
too improbable. It should be noted that in inertial confinement, both stellar densities
and temperatures are exceeded to compensate for the shortcomings of the third
parameter of the Lawson criterion, ICF's very short confinement time.
• have two or more products - This allows simultaneous conservation of energy and
momentum without relying on the (weak!) electromagnetic force.
• conserve both protons and neutrons - The cross sections for the weak interaction are
too small.
Few reactions meet these criteria. The following are those with the largest cross-sections:
Table 1. Suitable reactions for thermonuclear fusion
p (protium), D (deuterium), and T (tritium) are shorthand notation for the main three isotopes of
hydrogen.
For reactions with two products, the energy is divided between them in inverse
proportion to their masses, as shown. In most reactions with three products, the distribution of
energy varies. For reactions that can result in more than one set of products, the branching
ratios are given.
Some reaction candidates can be eliminated at once. The D6
Li reaction has no advantage
compared to p11B
because it is roughly as difficult to burn but produces substantially more
neutrons through D-D side reactions. There is also a p7
Li reaction, but the cross-section is far
too low except possible for Ti > 1 MeV, but at such high temperatures an endothermic, direct
neutron-producing reaction also becomes very significant. Finally there is also a p9Be
New Concepts, Ideas and Innovations in Aerospace… 235
reaction, which is not only difficult to burn, but 9Be can be easily induced to split into two
alphas and a neutron.
In addition to the fusion reactions, the following reactions with neutrons are important in
order to "breed" tritium in "dry" fusion bombs and some proposed fusion reactors:
n + 6
Li → T + 4He ,
n + 7
Li → T + 4He + n .
To evaluate the usefulness of these reactions, in addition to the reactants, the products,
and the energy released, one needs to know something about the cross section. Any given
fusion device will have a maximum plasma pressure that it can sustain, and an economical
device will always operate near this maximum. Given this pressure, the largest fusion output
is obtained when the temperature is selected so that <σv>/T² is a maximum. This is also the
temperature at which the value of the triple product nTτ required for ignition is a minimum.
This chosen optimum temperature and the value of <σv>/T² at that temperature is given for a
few of these reactions in the following table.
Table 2. Optimum temperature and the value of <σv>/T² at that temperature
fuel T [keV] <σv>/T² [m³/s/keV²]
D-T 13.6 1.24×10-24
D-D 15 1.28×10-26
D3He
58 2.24×10-26
p6Li
66 1.46×10-27
p11B
123 3.01×10-27
Note that many of the reactions form chains. For instance, a reactor fueled with T and 3He will create
some D, which is then possible to use in the D + 3He reaction if the energies are "right". An elegant idea
is to combine the reactions (8) and (9). The 3He from reaction (8) can react with 6
Li in reaction (9)
before completely thermalizing. This produces an energetic proton which in turn undergoes reaction (8)
before thermalizing. A detailed analysis shows that this idea will not really work well, but it is a good
example of a case where the usual assumption of a Maxwellian plasma is not appropriate.
Any of the reactions above can, in principle, be the basis of fusion power production. In
addition to the temperature and cross section discussed above, we must consider the total
energy of the fusion products Efus, the energy of the charged fusion products Ech, and the
atomic number Z of the non-hydrogenic reactant.
Specification of the D-D reaction entails some difficulties, though. To begin with, one
must average over the two branches (2) and (3). More difficult is to decide how to treat the T
and 3He products. T burns so well in a deuterium plasma that it is almost impossible to extract
from the plasma. The D3He
reaction is optimized at a much higher temperature, so the burnup
at the optimum D-D temperature may be low, so it seems reasonable to assume the T but
not the 3He gets burned up and adds its energy to the net reaction. Thus we will count the D-D
fusion energy as Efus = (4.03+17.6+3.27)/2 = 12.5 MeV and the energy in charged particles as
Ech = (4.03+3.5+0.82)/2 = 4.2 MeV.
236 Alexander Bolonkin
Another unique aspect of the D-D reaction is that there is only one reactant, which must
be taken into account when calculating the reaction rate.
With this choice, we tabulate parameters for four of the most important reactions.
Table 3. Parameters of the most important reactions
Fuel Z Efus [MeV] Ech [MeV] neutronicity
D-T 1 17.6 3.5 0.80
D-D 1 12.5 4.2 0.66
D3He
2 18.3 18.3 ~ 0.05
p11B
5 8.7 8.7 ~ 0.001
The last column is the neutronicity of the reaction, the fraction of the fusion energy
released as neutrons. This is an important indicator of the magnitude of the problems
associated with neutrons like radiation damage, biological shielding, remote handling, and
safety. For the first two reactions it is calculated as (Efus-Ech)/Efus. For the last two reactions,
where this calculation would give zero, the values quoted are rough estimates based on side
reactions that produce neutrons in a plasma in thermal equilibrium.
Of course, the reactants should also be mixed in the optimal proportions. This is the case
when each reactant ion plus its associated electrons accounts for half the pressure. Assuming
that the total pressure is fixed, this means that density of the non-hydrogenic ion is smaller
than that of the hydrogenic ion by a factor 2/(Z+1). Therefore the rate for these reactions is
reduced by the same factor, on top of any differences in the values of <σv>/T². On the other
hand, because the D-D reaction has only one reactant, the rate is twice as high as if the fuel
were divided between two hydrogenic species.
Thus, there is a "penalty" of (2/(Z+1)) for non-hydrogenic fuels arising from the fact that
they require more electrons, which take up pressure without participating in the fusion
reaction. There is, at the same time, a "bonus" of a factor 2 for D-D due to the fact that each
ion can react with any of the other ions, not just a fraction of them.
We can now compare these reactions in the following table 4.
Table 4. Comparison of reactions
fuel <σv>/T² penalty/
bonus reactivity Lawson
criterion
power
density
D-T 1.24×10-24 1 1 1 1
D-D 1.28×10-26 2 48 30 68
D3He
2.24×10-26 2/3 83 16 80
p11B
3.01×10-27 1/3 1240 500 2500
The maximum value of <σv>/T² is taken from a previous table. The "penalty/bonus"
factor is that related to a non-hydrogenic reactant or a single-species reaction. The values in
the column "reactivity" are found by dividing (1.24×10-24 by the product of the second and
New Concepts, Ideas and Innovations in Aerospace… 237
third columns. It indicates the factor by which the other reactions occur more slowly than the
D-T reaction under comparable conditions. The column "Lawson criterion" weights these
results with Ech and gives an indication of how much more difficult it is to achieve ignition
with these reactions, relative to the difficulty for the D-T reaction. The last column is labeled
"power density" and weights the practical reactivity with Efus. It indicates how much lower
the fusion power density of the other reactions is compared to the D-T reaction and can be
considered a measure of the economic potential.
Bremsstrahlung (Brake) Losses
Bremsstrahlung, (from the German bremsen, to brake and Strahlung, radiation, thus,
"braking radiation"), is electromagnetic radiation produced by the acceleration of a charged
particle, such as an electron, when deflected by another charged particle, such as an atomic
nucleus. The term is also used to refer to the process of producing the radiation.
Bremsstrahlung has a continuous spectrum. The phenomenon was discovered by Nikola Tesla
(1856-1943) during high frequency research he conducted between 1888 and 1897.
Bremsstrahlung may also be referred to as free-free radiation. This refers to the radiation
that arises as a result of a charged particle that is free both before and after the deflection
(acceleration) that causes the emission. Strictly speaking, bremsstrahlung refers to any
radiation due to the acceleration of a charged particle, which includes synchrotron radiation;
however, it is frequently used (even when not speaking German) in the more literal and
narrow sense of radiation from electrons stopping in matter.
Table 5. Rough optimum temperature and the power ratio
of fusion and Bremsstrahlung radiation lost
Fuel Ti (keV) Pfusion/PBremsstrahlung
D-T 50 140
D-D 500 2.9
D3He
100 5.3
3He3He
1000 0.72
p6Li
800 0.21
p11B
300 0.57
The ions undergoing fusion will essentially never occur alone but will be mixed with
electrons that neutralize the ions' electrical charge and form a plasma. The electrons will
generally have a temperature comparable to or greater than that of the ions, so they will
collide with the ions and emit Bremsstrahlung. The Sun and stars are opaque to
Bremsstrahlung, but essentially any terrestrial fusion reactor will be optically thin at relevant
wavelengths. Bremsstrahlung is also difficult to reflect and difficult to convert directly to
electricity, so the ratio of fusion power produced to Bremsstrahlung radiation lost is an
important figure of merit. This ratio is generally maximized at a much higher temperature
than that which maximizes the power density (see the previous subsection). The following
238 Alexander Bolonkin
table shows the rough optimum temperature and the power ratio at that temperature for
several reactions.
The actual ratios of fusion to Bremsstrahlung power will likely be significantly lower for
several reasons. For one, the calculation assumes that the energy of the fusion products is
transmitted completely to the fuel ions, which then lose energy to the electrons by collisions,
which in turn lose energy by Bremsstrahlung. However because the fusion products move
much faster than the fuel ions, they will give up a significant fraction of their energy directly
to the electrons. Secondly, the plasma is assumed to be composed purely of fuel ions. In
practice, there will be a significant proportion of impurity ions, which will lower the ratio. In
particular, the fusion products themselves must remain in the plasma until they have given up
their energy, and will remain some time after that in any proposed confinement scheme.
Finally, all channels of energy loss other than Bremsstrahlung have been neglected. The last
two factors are related. On theoretical and experimental grounds, particle and energy
confinement seem to be closely related. In a confinement scheme that does a good job of
retaining energy, fusion products will build up. If the fusion products are efficiently ejected,
then energy confinement will be poor, too.
The temperatures maximizing the fusion power compared to the Bremsstrahlung are in
every case higher than the temperature that maximizes the power density and minimizes the
required value of the fusion triple product (Lawson criterion). This will not change the
optimum operating point for D-T very much because the Bremsstrahlung fraction is low, but
it will push the other fuels into regimes where the power density relative to D-T is even lower
and the required confinement even more difficult to achieve. For D-D and D3He,
Bremsstrahlung losses will be a serious, possibly prohibitive problem. For 3He3He,
p6
Li and
p11B
the Bremsstrahlung losses appear to make a fusion reactor using these fuels impossible.
In a plasma, the free electrons are constantly producing Bremsstrahlung in collisions with
the ions. The power density of the Bremsstrahlung radiated is given by
e e eff
e
Br n T Z
m
h
P
2 1/ 2
3/ 2
3 2
3
16
Te
is the electron temperature, α is the fine structure constant, h is Planck's constant, and
the "effective" ion charge state Zeff is given by an average over the charge states of the ions:
Zeff = Σ (Z² nZ) / ne
This formula is derived in "Basic Principles of Plasmas Physics: A Statistical Approach"
by S. Ichimaru, p. 228. It applies for high enough Te
that the electron deBroglie wavelength is
longer than the classical Coulomb distance of closest approach. In practical units, this formula
gives
P
Br
= (1.69×10-32 /W cm-3
) (ne
/cm-3
)
2
(Te
/eV)1/2 Zeff
= (5.34×10-37 /W m-3
) (ne /m-3
)
2
(Te
/keV)1/2 Zeff
New Concepts, Ideas and Innovations in Aerospace… 239
where Wcm-3
, cm
-3
, eV, Wm-3
, m
-3
, keV are units of correcponding magnitudes. For very high
temperatures there are relativistic corrections to this formula, that is, additional terms of order
Te
/mec
2
.
LIST OF MAIN EQUATIONS
Below are the main equations for estimation of benefits from the offered innovations.
1. Energy Needed for Thermonuclear Reaction
0 1 2
1 5 3
0
2
1 2
2
1 2
(1.2 1.5) 10 , ,
, , ,
0
r A A Z N r r r
r
kZ Z e
E Fdr E
r
Q Q
F k
i
r
(1)
where k = 9109
constant; Z1, Z2 are charge state of 1 and 2 particles respectively; e =
1,610-19 C is charge of electron; ro = r1 + r2 is sum of radius of nuclear force, m; A is number
of element; F is force, N; E is energy, J; Q is charge of particles.
For example, for reaction H+H (hydrogen, Z1 = Z2 =1, ro 210-15 m) this energy is 0.7
MeV or 0.35 MeV for every particle. The real energy is about 30 times less because part of
the particles has more average speed and there is a tunnel effect.
2. Energy Needed for Ignition. Figure 8 shows a magnitude n (analog of Lawson
criterion) required for ignition.
240 Alexander Bolonkin
Figure 8. Value n (analog of Lawson criterion) versus temperature in K. Value n is in s/cm3
, η is
efficiency coefficient.
At present the industry produces power lasers:
• Carbon dioxide lasers emit up to 100 kW at 9.6 µm and 10.6 µm, and are used in
industry for cutting and welding.
• Carbon monoxide lasers must be cooled but can produce up to 500 kW.
Special laser and ICF reastors:
• NOVA (1999, USA). Laser 100 kJ (wavelenght =105410-9 m) and 40 kJ
(wavelenght =35110-9 m), power few tens of terawatts (1 TW = 1012 W), time of
impulse (2 4) 10-9
s, 10-beams, Matter is Nd:class.
• OMERA (1995, USA). 60-beam, neodyminm class laser, 30 kJ, power 60 TW.
• Z-mashine (USA, under constructin), Power is up 350 TW. It can create currency
impuls up 20106 A.
• NIF (USA). As of 2005 the National Ignition Facility is working on a system that,
when complete, will contain 192-beam, 1.8-megajoule, 700-terawatt laser system
adjoining a 10-meter-diameter target chamber.
• 1.25 PW - world's most powerful laser (claimed on 23 May 1996 by Lawrence
Livermore Laboratory).
3. Radiation energy from hot solid black body is (Stefan-Boltzmann Law):
4 E T ,
(2)
where E is emitted energy, W/m2
; = 5.6710-8
- Stefan-Boltzmann constant, W/m2 oK
4
; T is
temperature in oK.
4. Wavelength corresponded of maximum energy density (Wien's Law) is
0
0
2
,
T
b
(3)
where b = 2.897810-3
is constant, m
oK; T is temperature, oK; is angle frequency of wave,
rad/s.
5. Pressure for Single Full Reflection is
F 2E / c , (4)
where F - pressure, N/m2
; c = 3108
is light speed, m/s, E is radiation power, W/m2
. If plasma
does not reflect radiation the pressure equals
New Concepts, Ideas and Innovations in Aerospace… 241
F = E/c. (5)
6. Pressure for Plasma Multi-Reflection [23-25] is
c q
E
F
1
2 2
,
(6)
where q is plasma reflection coefficient. For example, if q = 0.98 the radiation pressure
increases by 100 times. We neglect losses of prism reflection.
7. The Bremsstrahlung (Brake) Loss energy of plasma by radiation is (T > 106 oK)
PBr ne
T Zeff Zeff Z n
z
ne 5.34 10 , where ( )/
37 2 0.5 2
(7)
where PBr is power of Bremsstrahlung radiation, W/m3
; ne
is number of particles in m3
; T is a
plasma temperature, KeV; Z is charge state; Zeff is cross-section coefficient for multi-charges
ions. For reactions H+D, D+T the Zeff equals 1.
That loss may be very much. For some reaction they are more then useful nuclear energy
and fusion nuclear reaction may be stopped. The Bremsstrahlung emission has continuous
spectra.
8. Electron Frequency in Plasma is
in "cgs" units, or 56.4( ) in CI units
, or 5.64 10 ( )
4
1/ 2
4 1/ 2
1/ 2
2
n
n
m
n e
p e
p e e
e
e
p e
(8)
where pe is electron frequency, rad/s; ne
is electron density, [1/cm3
]; n is electron density,
[1/m3
]; me = 9.1110-28 is mass of electron, g; e = 1.610-19 is electron charge, C.
The plasma is reflected an electromagnet radiation if frequency of electromagnet
radiation is less then electron frequency in plasma, < pe. That reflectivity is high. For T >
15106 oK it is more than silver and increases with plasma temperature as T
3/2. The frequency
of laser beam and Bremsstrahlung emission are less then electron frequency in plasma.
9. The Deep of Penetration of outer radiation into plasma is
5 1/ 2
5.31 10
e
pe
p n
c
d
. [cm]
(9)
For plasma density ne = 1022 1/cm3
dp = 5.3110-6
cm.
10. The Gas (Plasma) Dynamic Pressure, pk
, is
242 Alexander Bolonkin
pk
nk(T
e
Ti
) if T
e
Tk
then pk
2nkT
(10)
where k = 1.3810-23 is Boltzmann constant; Te
is temperature of electrons, oK; Ti
is
temperature of ions, oK. These temperatures may be different; n is plasma density, 1/m3
; pk
is
plasma pressure, N/m2
.
11. The gas (plasma) ion pressure, p, is
p nkT
3
2
,
(11)
Here n is plasma density in 1/m3
.
12. The magnetic pm and electrostatic pressure, ps
, are
2
0
0
2
2
1
,
2
m ps
ES
B
p
(12)
where B is electromagnetic induction, Tesla; 0 = 410-7
electromagnetic constant; 0 =
8.8510-12 , F/m, is electrostatic constant; ES is electrostatic intensity, V/m.
13. Ion thermal velocity is
9.79 10 cm/s 5 1/ 2 1/ 2
1/ 2
i
i
i
Ti T
m
k T
v
, (13)
where = mi /mp , mi
is mass of ion, kg; mp = 1.6710-27 is mass of proton, kg.
14. Transverse Spitzer plasma resistivety
c m
T
0.1Z
1.03 10 ln , c m or 3/2
2 3/ 2
Z T ,
(14)
where ln = 5 15 10 is Coulomb logarithm, Z is charge state.
15. Reaction rates <v> (in cm3
s
-1
) averaged over Mexwellian distributions for low
energy (T < 25 keV) may be represent by
( ) 3.68 10 exp( 19.94 ) cm s ,
( ) 2.33 10 exp( 18.76 ) cm s ,
1 2 2 / 3 1/ 3 3 1
1 4 2 / 3 1/ 3 3 1
T T
T T
DT
DD
(15)
where T is measured in keV.
New Concepts, Ideas and Innovations in Aerospace… 243
16. The power density released in the form of charged particles is
12 3
13 3
13 2 3
2.9 10 ( ) , W cm
5.6 10 ( ) , W cm
3.3 10 ( ) , W cm
3 3 3
DHe D He DHe
DT D T DT
DD D DD
P n n
P n n
P n
(16)
Here in PDD equation it is included D + T reaction.
COMPUTED ESTIMATIONS OF AB-REACTORS
We consider two new Micro-AB-Reactors having the innovative: multi-reflect radiation
and self-magnetic confinement features.
In multi-reflect radiation confinement of AB-Reactor the offered innovation is the special
prisms, a high reflectivity mirror that returns the laser beam exactly to its point of origination.
As a result, the all energy absorbs by plasma, the laser radiation multi-times presses the
plasma and impedes it or, at least, it does not allow its expansion. The plasma has high
reflectivity and this press effect may be increased hundreds to thousands of times. Practically
speaking, we are weakly limited and can use the cheap and solid fuel.
The uniformly heating of target by laser beam is very big and important problem in ICF.
The non-equal rocket forces on target shell destroy the capsule before thermonuclear ignition.
If the first ICF reactor had some laser beams, the second generation had 10 laser beams
(NOVA), the third generation has 60 beams (OMEGA), and the next generation will have 192
beams (NIF). All laser beams must be equal and work in coordination - that is complex,
difficult and expensive problem. The prism reflector is easy designed such the reflected beam
runs round the target and presses it uniformly from all sides after 2 - 4 reflections.
The second innovation is the special form microcapsule that is filled by compression gas
or liquid (frozen) fuel.
In self-magnetic confinement Micro-AB-Reactor main innovation is super thin
microcapsule and electric heating which produce high-intensity magnetic field, keeping the
plasma pressure and conic (or close to conic) ends of ampoule capsule which work as plasma
stoppers. The important innovation is the using an electric currency for straight heating of
capsule. The magnetic lines in our reactor are circles located into and around plasma channel.
The magnetic intensity increases from central axis to maximal plasma radius. That pushes
plasma into center of plasma channel. In the ends of plasma channel the magnetic forces put
obstacles in plasma leakage.
For estimation possibilities of these innovations in the first AB-reactor we compute the
multi-reflection pressure, the condition of plasma reflection and compare them with dynamic
pressure of plasma. In the second AB-reactor we consider the equilibrium the magnetic and
kinetic pressures.
Capsules. For multi-reflex conformation is more suitable the spherical capsule. Let us
consider the gas compressed fuel capsule. The shell thickness and relative weight of gas
compressed fuel spherical capsule can be computed by equations:
244 Alexander Bolonkin
f
S
R
P M
P
r
2
3
,
2
,
(17)
where is shell thickness of capsula, [m]; r is capsule radius, [m[;/r is relative thickness of
fuel shell; P is fuel gas pressure into capsule (over the atmospheric pressure), [N/m2
]; is
safety tensile stress, N/m2
; MR is relative capsule mass; s
is density of capsule shell, [kg/m3
];
f
is density of fuel, [kg/m3
].
Example, for gas pressure P = 100 atm = 107 N/m2
, = 200 kgf/mm2
= 2109 N/m2
, s =
1800 kg/m3
; f = 11 kg/m3
(at P = 100 atm) we get /r = 2.510-3
, MR = 0.6.
Cylindrical capsula (l >> r). For our estimations we take the capsule having the length 1
mm, radius r = 0.05 mm, cross section area S 810-3
mm
3
, fuel volume Vc = 810-3
mm
3
=
810-12
m
3
. That is very small. It is a microcapsule.
If the gas in a microcapsule is pressed the relative thickness and relative mass of
cylindrical shell may be computed by equations:
f
s
R
P M
P
r
, 2 ,
(18)
For P = 100 atm (P = 107 N/m2
) and = 200 kg/mm2
( = 2109 N/m2
) ratio /r =
510-3
, MS = 1.3 .
Fuel density. The particles (ions) density n of fuel in 1 m3
and number of particles nC in
microcapsule equal
p
i
p
i
C C
p
f
i a
fa
a p
f f fa
p
m
m
m
m
n nV
m m m m
n
2
2
1
1
1
1
2
2
1
1
where ,
,
2
1
(19)
where mia =2.51.67210-27 kg for D+T is average mass of fuel ion; mp = 1.67210-27 kg is
proton mass; low indexes "1, 2" means the first and the second fuel component.
The n 1020 1/m3
in the present magnetic confinement fusion reactor; n 2.61025 1/ m3
for gas D+T in a pressure 1 atm, T = 288 oK (the density of deuterium D is f1 = 0.0875
kg/m3
, 1 = 2, the density of Tritium is 1.5 more). For D and other pressure the n must be
changed in same times, for example, if P = 100 atm then f = 8.75 kg/m3
, n 2.61027 1/m3
,
nc = 20.81015
; n 2.11028 1/m3
, nc = 1.71017 (f = 71 kg/m3
) for liquid hydrogen at a
pressure of 1 atm. (In conventional inertial confinement fusion reactor, the fuel density may
be more in 10 - 30 times, under a rocket pressure of a fuel capsule cover. For hydrogen the
frizzed temperature is -259.34 oC, the boiling point is -252.87 oC). For D+T average a =
(2+3)/2 = 2.5.
New Concepts, Ideas and Innovations in Aerospace… 245
Fuel mass Mf [kg] and thermonuclear energy EC into microcapsule are computed by
equations:
f N p C C C R
N
r
r f
N p
f
M m nV E nV E
E
E M
m
M
E
19
19 8
, 0.5 1.6 10
1.6 10 0.96 10 ,
(20)
where Er
is reaction energy of one couple particles, eV; N = 1 + 2 is number of nucleons
which take part in reaction, for D+T N = 2+3=5. If we want compute energy of one type of
particles, the Er
is reaction energy for given type of particles, for D+T the energy Er = 17.5
MeV;. For example, our capsule (10.1 mm) filled by liquid fuel D+T has fuel mass Mf =
0.7110-3
g and will produce energy Ec = 240 kJ. If we burn out 10 capsules per 1 s, the
engine power will be 2400 kW. An estimated 20% this energy gives the charged particles and
80% of neutrons. The fuel capsule having M = 10 g =10-5
kg of a mixture D+T produces
3.34109
J if all atoms take part in reaction. That is equivalent to the energy derived from 84
liters of benzene.
Computations are presented in Figure 9.
Figure 9. Energy of thermonuclear reactor versus the fuel mass and energy per one nucleon.
ER = Er
/N.
Distribution of thermonuclear energy between particles. In most cases the result of
thermonuclear reaction is two components. As you see in Table 1 that may be "He" and
neutron or proton. The thermonuclear energy distributes between them the following manner:
246 Alexander Bolonkin
2 1
1 2
2
1 2
1 2
1 1 2 2
2
2 2
2
1 1
1 2
we have ,
, ,
2 2
From
E E E
m m
m
E
E
mV m V
mV m V
E E E
(21)
where m is particle mass, kg; V is particle speed, m/s; E is particle energy, J; = mi /mp is
relative particle mass. Lower indexes "1, 2" are number of particles.
Unfortunately, as you can see (in Table 1), most particle energy catches the neutron as
the lightest particle. But its emission has high penetrating capability, creating radioactive
isotopes, causing damage to the main construction, very dangerous for living beings, and that
can be converted only in heat energy.
Energy is needed for fuel heating. This energy can be estimated by equation:
p
ia
a
p
k
a
h
m
m
m
k MT c
c
E
4.13 10 ,
2
,
3
(22)
where c is plasma thermal capacity, J/kg. oK; Tk
is temperature in oK; k is Boltzmann constant,
mia is average mass of ions, kg; M is fuel mass, kg. This computation is presented in Figure
10. Our capsule filled by liquid mixture D+T requests ignition energy about 124 J for its
heating up to 100 million oK. That is energy of electric condenser having size about
101010 cm for = 108 V/m (see below).
Figure 10. Energy requested for fuel D+T heating.
New Concepts, Ideas and Innovations in Aerospace… 247
Capacitor for thermonuclear ignition. Condenser requested as storage of energy for fuel
thermonuclear ignition my be estimated by equation
2
,
2
1
2
2 0
0
M
W
V
W
(23)
where W is condenser energy, J; V is condenser volume, m3
; M is condenser mass, kg; o =
8.8510-12 /m is the electrostatic constant; is dielectric constant; is dielectric strength,
V/m; is specific density of dielectric, kg/m3
. Energy from capacitor is about one joule from
one centimeter cub.
Electron plasma frequency. Electron frequency of plasma is computed by equation (8).
For n 1020 1/m3
that is equals pe = 5.641011 rad/s, for n 1028 1/m3
that equals pe =
5.641015 rad/s . That is more then the laser frequency ( = 0.310-9
m, = 2.11010 rad/s).
That means the plasma will reflect the laser beam.
Plasma skin depth. The depth in plasma to which an electromagnetic radiation can
penetrate (Eq. (9)) is: For n 1020 1/m3
that is equals dp = 5.3110-2
cm, for n 1028 1/m3
that equals dp = 5.3110-6
cm. As you see, the depth is small.
Coefficient reflectivity of plasma. No data about plasma reflectivity. However, from
general theory of reflectivity it is known the reflectivity depends from conductivity (see Eq.
(14)). Silver has the best conductivity from solid body and best reflectivity. It is about q =
0.78 0.99 (it depends from frequency of radiation: for ultra-violet radiation q 0.78, for
thermal radiation q 0.99). The plasma for T > 15106 oK has better conductivity then silver.
The plasma conductivity increases as T
3/2. That means the plasma having the T 108 oK has
reflectivity in 17.2 times better then silver. That means the plasma reflectivity is more 0.999.
We take in our computation q = 0.999. The efficiency of offered innovation very strong
depends from reflectivity of plasma. The reflectivity of the prism mirror is very high [23]. We
neglect the loss in it.
Bremsstrahlung (brake) radiation. That is proportional the energy spectra E and has
Maxwell distribution:
h
c c E
dE
k T
E
k E
E
dE
dE
dP f dE f
k
E p
,
exp ,
( )
2 3
(24)
where k = 1,3810-23 is Boltzmann's constant, J/oK; T - temperature, oK; E - energy, J; -
frequency, 1/s; length of wave, m; h = 6.52510-34 is Planck's constant, J.
s. Assume the
brake radiation has same specter.
Computations are presented in figures 11-12.
248 Alexander Bolonkin
Figure 11. Spectra of brake radiation for plasma temperature 60 - 200 millions degrees (oK).
Figure 12. Spectra of brake radiation for plasma temperature 200 - 1000 millions degrees (oK).
The ultra-violet rays are below approximately < 31017 hertz ( >10-9 m), the soft x-rays
are below < 31019 hertz ( >10-11 m). That means the brake radiation can be reflected by
special methods. For example, the silver having high electro-conductivity has average
reflectivity 0.99 in heat region, 0.95 in light region, and 0.78 in ultra-violet region. Some
New Concepts, Ideas and Innovations in Aerospace… 249
metals has reflectivity up 0.2 for = 4010-9
m. But plasma having the temperature more than
15106 oK has more electro-conductivity then silver and it must, therefore, have better
reflectivity. The reflectivity coefficient of prism mirror is very high and we can neglect its
losses. However, the reflectivity of prism mirror for brake radiation is needed in a detailed
test.
The average energy of Bremsstrahlung photon equals average energy of plasma electron.
The formula for average wavelength is:
k k
e
k
k T T
ch
c
E k T h
0.0144
w e receive
From ,
(25)
where E is electron energy, c = 3108
is light speed, m/s; Tk is temperature in oK; e
is wave
length, m ; is wave frequency, 1/s;.
For example, for Tk = 108 oK the e = 1.4410-10 m. That value is the lower ultra-violet
diapason > 10-9
m.
For very high temperature the most part of this spectrum is in the soft x-ray region, but
soft x-ray can be reflected and retracted by special methods.
The reactive pressure. We can estimate that the ion speed for T =108 oK. That is
approximately V = 600 km/s. If M = 0.1 g =10-7
kg of a mixture D+T is increased their
speed to this value in time =10-9
s, the reactive force will be F = MV/ 5107 N. If the fuel
capsule has surface s = 5 mm2
= 510-6
m
2
the capsule cover pressure is p = F/s = 1013 N/m2
= 108
atm. This pressure produces the shockwave which compresses the fuel microcapsule
and create high ion temperature.
RADIATION CONFINEMENT
Radiation confinement is suitable for multi-reflex laser beam support.
Equilibrum of Multi-Reflex Laser and Kinetic Pressures
From equations (6), (10) we receive
0.5 (1 )
, ,
1
2 2
2 ,
P SE nkT cS q
P P
c q
E
P nkT P
L k
k k R k R
(26)
where PL is impulse power of laser, W; S is surface of capsule or plasma; q is plasma
reflection. The additional number 2 appears because we neglect the prism reflection loss. The
250 Alexander Bolonkin
computations for n = (0 1)1028 1/m3
, S = (1 4)10-6
m
2
, q = 0.999, Tk = 108
are presented
in Figure 13.
Figure 13. Equilibrium of multi-reflex laser pulse power versus plasma density and fuel capsule surface
S for coefficient plasma reflectivity q = 0.999, plasma temperature Tk = 108 oK.
Look your attention that power of laser pulse for multi-reflection confinement is in tens -
hundreds times less then one is in the current ICF reactors (OMEGA has 601012 W, Zmachine
will have 3501012 W). That shows, the multi-reflect conformation is more
efficiency then rocket conformation for small targets.
We can increase the initial multi-reflex pressure in millions times if we cover the outer
capsule surface the small reflective prism as internal surface of the combustion chamber. As it
is shown in [26] p. 378, Figure A3.4, the pressere from 1 kW of laser power can reach more
104 N. If laser pulse power has PL= 1013 W, the pressure will be F = 1017 N. The surface of a
spherical capsule having diameter 1 mm is about S = 3 mm2
=310-6
m
2
. Hence the pressure
on target is P = F/S =3.31022 N/m2
= 3.31017 atm! That is in 109
times more then a gas
dynamic pressure of the plasma at temperature 108 K.
Note. The rocket force used for compressing and heating pullet at present time cannot
keep the big pressure and temperature for very small capsules at need time because gas
extension. For example, let us to estimate the extension time for two capsules having diameter
d = 0.3 mm and d = 3 mm respectively at temperature 108 K. The average ion speed at this
temperature is about 6105 m/s. For typical pulse time 10-9
s the plasma radius is increased in
610-4 m = 0.6 mm. That means the volume of the first capsule increases in (0.75/0.15)3
=
125 times, the volume of the second capsule is increased only in (2.1/1.5)3
= 2.7 times. In our
multi-reflex reactor the beam pressure does not allow to expansion the plasma and increases
the reaction time and possibility thermonuclear reaction in hundreds times.
New Concepts, Ideas and Innovations in Aerospace… 251
Requested minimum time of laser pulse. Duration of laser pulse needed for heating of
capsule can be computed by equation
L
f k
P
c1M T
(27)
where c1 = 4.13103
is thermal capacity coefficient, J/kg.K; Tk
is plasma temperature, K.
The computations are presented in Figure 14.
Figure 14. Request laser pulse time for capsule heating via capsule mass and laser pulse power for
capsule temperature 108 K.
As you see, the pulse is same with current laser (1 10)10-12 s, (ps). In conventional
ICF reactor the most part beam energy is reflected by plasma and heating the shell of
combustion chamber. In our reactor the nearly all beam energy is used for capsule heating.
Equilibrium of Brake Radiation and Kinetic Pressures
From equations (10), (7) we receive
eff
e
e
k
eff
k k BP e eff k BP
V Z
S
q T
T
T
V Z
k c q S
n
n T Z P P
c q S
V
P nkT P
28 1/ 2
37 1/ 2
37 2 1/ 2
9 10 (1 )
5.34 10
(1 )
5.34 10 , ,
(1 )
2
2 ,
(28)
252 Alexander Bolonkin
where Te
is temperature in keV; V is plasma volume, m3
; S is plasma surface, m2
; q is average
coefficient reflectivity of x-rays produced by brake radiation. The equilibrium of brake
radiation and kinetic pressure can be reached for ratio V/S 1.
THE SELF-MAGNETIC CONFINEMENT
The self-magnitude confinement is suitable for low-density plasma. Your attention is
called for to the big difference between a present conventional reactor magnetic field and the
offered self-magnetic field. For creating of the present magnetic field, the large powerful
superconductivity very expensive magnets are used. Our self-magnetic does not request
anything. The self-magnetic field is produced by capsule electric current and that is more
powerful by hundreds of times. Why? The magnetic intensity and pressure of electric current
in inverse proportion of plasma radius (see equations (29) below). The present thermonuclear
reactor has plasma camera of some meters. Our capsule has radius only 0.05 mm.
Equilibrium of Self-Magnetic and Kinetic Plasma Pressure
From equation (10) and (12) we receive
r
I
r nT U R I B
knT I r
r
I
P
r
I H
H
P P P nkT P
k
k
k m k k m m
2
4 4.16 10 ( ) , ,
,
8
,
2
,
2
, 2 ,
8 0.5 0
0
2
2
0
2
0
(29)
where r is radius of capsule (plasma flux), m; I is electric currency, A; R is capsule (plasma)
resistance, Ohm; U is capsule (electrodes) voltage, V; H is magnetic intensity, A/m; B is
magnetic intensity, Tesla; Tk
is plasma temperature , oK.
The computations for several n are presented in figures 15 - 18.
Figure 15. Equilibrium self-magnetic and kinetic pressures versus plasma temperature and plasma
densities. Capsule 0.11 mm. N is plasma density, 1/m3
.
New Concepts, Ideas and Innovations in Aerospace… 253
Note: This pressure is same for multi-reflex and plasma pressure.
Figure 16. Electric currency needed for equilibrium kinetic and magnetic pressure for several plasma
densities. Microcapsule has size 0.11 mm. N is plasma density, 1/m3
.
Figure 17. Electric voltage needed for equilibrium kinetic and magnetic pressures for several plasma
densities. Capsule has size 0.11 mm. N is plasma density, 1/m3
.
254 Alexander Bolonkin
Figure 18. Equilibrium self-magnetic intensity on microcapsule surface via plasma temperature for
several plasma densities. Capsule has size 0.11 mm. N is plasma density, 1/m3
.
The present magnetic confinement reactor having superconductivity magnets has
maximum magnetic intensity 5 - 6 Tesla. As you see in Figure 18 the offered AB-selfmagnetic
reactor has more magnetic intensity in hundreds times.
PROJECTS
Below there are estimations of some projects, which show parameters of suggested ABreactors.
These are not optimal reactors. They demonstrate the methods of computations and
possible technical data of new micro reactors.
1. Multi-reflection AB-reactor. Let us to take the spherical fuel capsule diameter d = 1
mm. Its surface is 3.14 mm2
, the volume is v = 0.52 mm3
= 5,210-10
m
3
. If gaseous fuel
(D+T) has pressure 1, 10, 100 atm, the specific fuel density are = 0.11 kg/m3
, 1.1 kg/m3
, 11
kg/m3
respectively. The fuel mass are Mf = = 5.710-11
, 5710-11
, 57010-11 kg
respectively. Particle densities are n1 = /a
.mp = 2.631025 1/m3
, 2.631026 1/m3
, 2.631027
1/m3
respectively. Numbers of particles in the capsule are n = n1v = 1.371016
, 1.371017
,
1.371018
respectively.
Thermonuclear energy in capsule are E = 0.5nE1 = 1.9104
J, 1.9105
J, 1.9106
J
respectively. Here E1 = 17.6106
1.610-19 = 2.810-12 J is the energy in single reaction of
couple particles. Where 17.6106 MeV is thermonuclear energy of reaction D+T. If we burn 1
capsule in 1 second, the thermonuclear power will be W = 1.9104 W, 1.9105 W, 1.9106 W
respectively.
Fuel heating energy are Ef = c1MfTk = 24 J, 240 J, 2400 J respectively. Here c1 =
4.13103
is average thermal capacity of plasma, Tk = 108 K is maximal plasma temperature.
New Concepts, Ideas and Innovations in Aerospace… 255
These heating energy must be increased some (3 6) times because we must to heat the
capsule shell and coefficient of energy efficiency is less then 1. The current condensers have
energy storage capability about 1 J/cm3
.
Requested minimum (equilibrium) pulse laser power equal N = 17.1109 W, 17.11010
W, 17.11011 W respectively (Eq. (22)) for q = 0.999. Pulse time is = Ef /N = 1.410-9
s.
We can use the liquid fuel. All parameter significantly will improvement (approximately
in 10 times with comparison of the 100 atm capsule), but we get a problem with storage of
capsules into a liquid helium.
2. Self-magnetic AB-reactor. Let us to take the fuel capsule of the length L = 1 mm,
diameter 2r = 0.1 mm and gaseous fuel (D+T) pressure p = 100 atm . The cross-section of
capsule is S = 7.8510-3
mm
2
, volume v = 7.8510-12
m
3
, fuel mass is Mf = = 9.510-11 kg,
particle density is n1 = /a
.mp = 2.631027 1/m3
, number of particle into capsule is n = n1v =
2.061016. Heating fuel energy is Ef = c1 Mf Tk = 39 J, for Tk = 108 K. If we burn 1 capsule in
1 second the thermonuclear power will be W = 3104 W.
Requested minimum (equilibrium) electric currency equal I = 1.07106 A (for Tk = 108
K),(Eq. (29)). The plasma electric specific resistance at Tk = 108 K is = 0.1Z/T3/2
=
1.2310-7 cm. The electric plasma resistance is Rf = L/S = 1.510-4 (all for Tk = 108 K).
Voltage U = IRf = 160 V. Pulse power N = IU = 17.1107 W. Pulse time is = 2.310-6
s.
Maximum intensity of magnetic field is B = oI/2r = 4280 T.
DISCUSSION
The offered thermonuclear AB-Reactors, as with any innovations, are needed in further
more detailed laboratory research, product development and testing. However, theses new
Reactors have gigantic advantages over present-day thermonuclear reactors:
(1) They are cheaper by many hundreds of times. That means not only non-industrial
countries but middle-size companies can undertake RandD and production of
perfected new thermonuclear reactors.
(2) They have a small weight and size but they have enough power (up 10,000 kW).
That means they can be used as engine of land vehicles, small ships, aircraft, manned
and unmanned spacecraft propulsion and community power utilities.
(3) They are not limited in high temperature regime as are all existing reactors. That
means they can use inexpensive fuel (not deuterium, tritium, helium-3, uranium as do
extant reactors).
The parameters of AB-Reactors are considered and computed in given article very far
from optima. They are only examples utilized to vividly illustrate the large possibilities of the
innovative reactors.
The suggested AB-thermonuclear reactor has Lawson criterion in some order more then
conventional current (2005) thermonuclear reactors (ICF). That strongly increases either of
three multipliers in Lawson criterion. That increases the density n up to two-three orders. It
increases the temperature T. It returns the laser and thermal radiation back to fuel pellet. (This
emission is lost in present reactors). It increases the time of reaction . The suggested AB
thermonuclear reactors may be a revolutionary jump in energy industry.
256 Alexander Bolonkin
Note: In conventional ICF the initial (internal into plasma) radiation does not compress
the plasma. Plasma is transparency for internal radiation. That emission influences only to an
emitted particle. When radiation came out of source (fuel pellet) and reflected or adsorbed by
chamber surface that does not press on pellet surface. By that means, the conventional inertial
thermonuclear reactor has only losses from radiation. The offered AB Reactor has the big
desirable benefits from thermal radiation. The more radiation, the more benefits.
The offered AB-Reactor can also have problems. The radiation mirror can have a bad
reflectivity for ultra-violent rays or experimenters may have problems with fast high-intensity
electric impulse through small capsule. However, if mirror will be reflect only conventional
ultra-violet, light, and thermal radiations that would be enough for ignition of a thermonuclear
reaction. As any innovation the offered reactor needs further perfecting RandD.
The offered AB-self magnetic reactor is different from present magnetic confinement
reactor. That is smaller because AB-self-magnetic reactor works a small fuel capsule. In
present-day reactor, the rare fuel gas (D+T) fills all volume of large chamber. In AB-Reactor
the fuel is located into small capsule under high pressure (or, as solid, liquid or frizzed fuel
under conventional pressure). In this case the fuel density can reach n = 10-26
10-27 1/m3
(or
solid, liquid, frozen fuel may be inside conductive matter, n = 10-28
10-29 1/m3
). If the
plasma reflectivity is high (q > 0,99), that is enough for thermonuclear ignition and keeping
plasma under the radiation pressure and magnetic pressure. For current MCF the magnetic
intensity is 5 T. For AB-Self-MCF the magnetic intensity may be about 104
T. For ABradiation
reactor the radiation pressure is about 1010
1013 N/m2
(millions atm) (Figure15).
We can neglect the outer magnetic force in AB-Reactor and we may design AB-Self-MCF
reactor without very complex and expensive superconductivity magnetic system.
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: Bolonkin, and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Bolonkin, A.A., (1982a), Installation for Open Electrostatic Field, Russian patent
application #3467270/21 116676, 9 July, 1982 (in Russian), Russian PTO.
[2] Bolonkin, A.A., (1982b), Radioisotope Propulsion. Russian patent application
#3467762/25 116952, 9 July 1982 (in Russian), Russian PTO.
[3] Bolonkin, A.A., (1982c), Radioisotope Electric Generator. Russian patent application
#3469511/25 116927. 9 July 1982 (in Russian), Russian PTO.
[4] Bolonkin, A.A., (1983a), Space Propulsion Using Solar Wing and Installation for It,
Russian patent application #3635955/23 126453, 19 August, 1983 (in Russian), Russian
PTO.
[5] Bolonkin, A.A., (1983b), Getting of Electric Energy from Space and Installation for It,
Russian patent application #3638699/25 126303, 19 August, 1983 (in Russian), Russian
PTO.
[6] Bolonkin, A.A., (1983c), Protection from Charged Particles in Space and Installation
for It, Russian patent application #3644168 136270, 23 September 1983, (in Russian),
Russian PTO.
New Concepts, Ideas and Innovations in Aerospace… 257
[7] Bolonkin, A. A., (1983d), Method of Transformation of Plasma Energy in Electric
Current and Installation for It. Russian patent application #3647344 136681 of 27 July
1983 (in Russian), Russian PTO.
[8] Bolonkin, A. A., (1983e), Method of Propulsion using Radioisotope Energy and
Installation for It. of Plasma Energy in Electric Current and Installation for it. Russian
patent application #3601164/25 086973 of 6 June, 1983 (in Russian), Russian PTO.
[9] Bolonkin, A. A.,(1983f), Transformation of Energy of Rarefaction Plasma in Electric
Current and Installation for it. Russian patent application #3663911/25 159775, 23
November 1983 (in Russian), Russian PTO.
[10] Bolonkin, A. A., (1983g), Method of a Keeping of a Neutral Plasma and Installation
for it. Russian patent application #3600272/25 086993, 6 June 1983 (in Russian),
Russian PTO.
[11] Bolonkin, A.A.,(1983h), Radioisotope Electric Generator. Russian patent application
#3620051/25 108943, 13 July 1983 (in Russian), Russian PTO.
[12] Bolonkin, A.A., (1983i), Method of Energy Transformation of Radioisotope Matter in
Electricity and Installation for it. Russian patent application #3647343/25 136692, 27
July 1983 (in Russian), Russian PTO.
[13] Bolonkin, A.A., (1983j), Method of stretching of thin film. Russian patent application
#3646689/10 138085, 28 September 1983 (in Russian), Russian PTO.
[14] Bolonkin A.A., (1983k), Light Pressure Engine, Patent (Author Certificate) No.
11833421, 1985 USSR (priority on 5 January 1983).
[15] Bolonkin, A.A., (1987), ―New Way of Thrust and Generation of Electrical Energy in
Space‖. Report ESTI, 1987, (Soviet Classified Projects).
[16] Bolonkin, A.A., (1990), ―Aviation, Motor and Space Designs‖, Collection Emerging
Technology in the Soviet Union, 1990, Delphic Ass., Inc., pp.32–80 (English).
[17] Bolonkin, A.A., (1991), The Development of Soviet Rocket Engines, 1991, Delphic
Ass.Inc., 122 p., Washington, (in English).
[18] Bolonkin, A.A., (1992a), ―A Space Motor Using Solar Wind Energy (Magnetic Particle
Sail)”. The World Space Congress, Washington, DC, USA, 28 Aug. – 5 Sept., 1992,
IAF-0615.
[19] Bolonkin, A.A., (1992b), ―Space Electric Generator, run by Solar Wing‖. The World
Space Congress, Washington, DC, USA, 28 Aug. – 5 Sept. 1992, IAF-92-0604.
[20] Bolonkin, A.A., (1992c), ―Simple Space Nuclear Reactor Motors and Electric
Generators Running on Radioactive Substances‖, The World Space Congress,
Washington, DC, USA, 28 Aug. – 5 Sept., 1992, IAF-92-0573.
[21] Bolonkin, A.A. (1994), ―The Simplest Space Electric Generator and Motor with
Control Energy and Thrust‖, 45th International Astronautical Congress, Jerusalem,
Israel, 9–14 Oct.,1994, IAF-94-R.1.368.
[22] Bolonkin A.A. (2004a), Light Multi-reflex Engine, JBIS, vol. 57, No. 9/10, 2004, pp.
353-359.
[23] Bolonkin A.A.(2004b), Multi-reflex Space Propulsion, JBIS, Vol. 57, No. 11/12, 2004,
pp. 379-390.
[24] Bolonkin A.A. (2006a), Non-Rocket Space Launch and Flight, Elsevier, London, 2006,
488 pgs.
[25] Bolonkin A.A. (2006b), New Thermonuclear Reactor, AIAA-2006-7225, Conference
"Space-2006", USA.
258 Alexander Bolonkin
[26] Bolonkin, A.A. (2006d). Electrostatic AB-Ramjet Space Propulsion, AIAA-2006-6173.
http://arxiv.org.
[27] Bolonkin A.A., (2006d). Beam Space Propulsion, AIAA-2006-7492. AEAT, Vol.78,
No. 6, 2006, pp. 502-508.
[28] Bolonkin A.A., (2006f). Electrostatic Linear Engine, AIAA-2006-4806. http://arxiv.org
Bolonkin A.A., (2006g). Suspended Air Surveillance System, AIAA-2006-6511.
http://arxiv.org.
[29] Bolonkin A.A., (2006h). Optimal Solid Space Tower (Mast), http://arxiv.org.
New Concepts, Ideas and Innovations in Aerospace…
Attachment to Part B, Ch.1. Possible thermonuclear propulsion
260 Alexander Bolonkin
Chapter 2
UTILIZATION OF WIND ENERGY AT
HIGH ALTITUDE
ABSTRACT
Ground based, wind energy extraction systems have reached their maximum
capability. The limitations of current designs are: wind instability, high cost of
installations, and small power output of a single unit. The wind energy industry needs of
revolutionary ideas to increase the capabilities of wind installations. This article suggests
a revolutionary innovation which produces a dramatic increase in power per unit and is
independent of prevailing weather and at a lower cost per unit of energy extracted. The
main innovation consists of large free-flying air rotors positioned at high altitude for
power and air stream stability, and an energy cable transmission system between the air
rotor and a ground based electric generator. The air rotor system flies at high altitude up
to 14 km. A stability and control is provided and systems enable the changing of altitude.
This chapter includes six examples having a high unit power output (up to 100
MW). The proposed examples provide the following main advantages: 1. Large power
production capacity per unit - up to 5,000-10,000 times more than conventional groundbased
rotor designs; 2. The rotor operates at high altitude of 1-14 km, where the wind
flow is strong and steady; 3. Installation cost per unit energy is low. 4. The installation is
environmentally friendly (no propeller noise).
Keywords: wind energy, cable energy transmission, utilization of wind energy at high
altitude, air rotor, windmills, Bolonkin.
Presented as Bolonkin‘s papers in International Energy Conversion Engineering Conference at Providence., RI,
Aug.16-19. 2004. AIAA-2004-5705, AIAA-2004-5756, USA.
New Concepts, Ideas and Innovations in Aerospace… 261
NOMENCLATURE (IN METRIC SYSTEM)
A - front area of rotor [m2
];
= 0.1 - 0.25 exponent of wind coefficient. One depends from Earth‘s surface
roughness;
Aa - wing area is served by aileron for balance of rotor (propeller) torque moment [m2
];
Aw - area of the support wing [m2
];
C - retail price of 1 kWh [$];
c - production cost of 1 kWh [$];
CL - lift coefficient (maximum CL 2.5);
CD – drag coefficient;
CL,a - difference of lift coefficient between left and right ailerons;
D – drag force [N];
Dr - drag of rotor [N];
E - annual energy produced by flow installation [J];
F – annual profit [$];
Ho = 10 m - standard altitude of ground wind installation [m];
H - altitude [m];
I - cost of Installation [$];
K1 - life time (years);
K2 – rotor lift coefficient (5-12 [kg/kW]);
L - length of cable [m];
Ly – lift force of wing [N];
M – annual maintenance [$];
N– power [W, joule/sec];
No - power at Ho ;
r - distance from center of wing to center of aileron [m];
R - radius of rotor (turbine)[m];
S - cross-section area of energy transmission cable [m2
];
V - annual average wind speed [m/s];
Vo - wind speed at standard altitude 10 m [m/s](Vo= 6 m/s);
W - weight of installation (rotor + cables)[kg];
Wy – weight of cable [kg];
- specific density of cable [kg/m3
];
- efficiency coefficient;
- angle between main (transmission) cable and horizontal surface;
- ratio of blade tip speed to wind speed;
v - speed of transmission cable [m/s];
- density of flow, =1.225 kg/m3
for air at sea level altitude H = 0; =0.736 at altitude
H =5 km;
= 0.413 at H =10 km;
- tensile stress of cable [N/m2
].
262 Alexander Bolonkin
INTRODUCTION
Wind is a clean and inexhaustible source of energy that has been used for many centuries
to grind grain, pump water, propel sailing ships, and perform other work. Wind farm is the
term used for a large number of wind machines clustered at a site with persistent favorable
winds, generally near mountain passes. Wind farms have been erected in New Hampshire, in
the Tehachapi Mountains. at Altamont Pass in California, at various sites in Hawaii, and may
other locations. Machine capacities range from 10 to 500 kilowatts. In 1984 the total energy
output of all wind farms in the United States exceeded 150 million kilowatt-hours.
A program of the United States Department of Energy encouraged the development of
new machines, the construction of wind farms, and an evaluation of the economic effect of
large-scale use of wind power.
The utilization of renewable energy (‗green‘ energy) is currently on the increase. For
example, a lot of wind turbines are being installed along the British coast. In addition, the
British government has plans to develop off-shore wind farms along their coast in an attempt
to increase the use of renewable energy sources. A total of $2.4 billion was injected into
renewable energy projects over the last three years in an attempt to meet the government's
target of using renewable energy to generate 10% of the country's energy needs by 2010.
This British program saves the emission of almost a millions tons of carbon dioxide.
Denmark plans to get about 30% of their energy from wind sources.
Unfortunately, current wind energy systems have deficiencies which limit their
commercial applications:
1. Wind energy is unevenly distributed and has relatively low energy density. Huge
turbines cannot be placed on the ground, many small turbines must be used instead.
In California, there are thousands of small wind turbines. However, while small
turbines are relatively inefficient, very huge turbines placed at ground are also
inefficient due to the relatively low wind energy density and their high cost. The
current cost of wind energy is higher then energy of thermal power stations.
2. Wind power is a function of the cube of wind velocity. At surface level, wind has
low speed and it is non-steady. If wind velocity decreases in half, the wind power
decreases by a factor of 8 times.
3. The productivity of a wind-power system depends heavily on the prevailing weather.
4. Wind turbines produce noise and visually detract from the landscape.
There are many research programs and proposals for the wind driven power generation
systems, however, all of them are ground or tower based. System proposed in this article is
located at high altitude (up to the stratosphere), where strong permanent and steady streams
are located. The also proposes a solution to the main technologist challenge of this system;
the transfer of energy to the ground via a mechanical transmission made from closed loop,
modern composite fiber cable.
The reader can find the information about this idea in [1], the wind energy in references
[2]-[3], a detailed description of the innovation in [4]-[5], and new material used in the
proposed innovation in [6]-[9]. The application of this innovation and energy transfer concept
to other fields can be found in [10]-[19].
New Concepts, Ideas and Innovations in Aerospace… 263
DESCRIPTION OF INNOVATION
Main proposed high altitude wind system is presented in Figure1. That includes: rotor
(turbine) 1, support wing 2, cable mechanical transmission and keep system 3, electrogenerator
4, and stabilizer 5. The transmission system has three cables (Figure1e): main
(central) cable, which keeps the rotor at a given altitude, and two transmission mobile cables,
which transfer energy from the rotor to the ground electric generator. The device of Figure1f
allows changing a cable length and a rotor altitude. In calm weather the rotor can be support
at altitude by dirigible 9 (Figure1c) or that is turned in vertical position and support by
rotation from the electric generator (Figure1d). If the wind is less of a minimum speed for
support of rotor at altitude the rotor may be supported by autogiro mode in position of
Figure1d. The probability of full wind calm at a high altitude is small and depends from an
installation location.
Figure2 shows other design of the proposed high altitude wind installation. This rotor has
blades, 10, connected to closed-loop cables. The forward blades have a positive angle and lift
force. When they are in a back position the lift force equals zero. The rotor is supported at the
high altitude by the blades and the wing 2 and stabilizer 5. That design also has energy
transmission 3 connected to the ground electric generator 4.
Figure3. shows a parachute wind high altitude installation. Here the blades are changed
by parachutes. The parachutes have a large air drag and rotate the cable rotor 1. The wind 2
supports the installation in high altitude. The cable transmission 3 passes the rotor rotation to
the ground electric generator 4.
A system of Figure4 uses a large Darries air turbine located at high altitude. This turbine
has four blades. The other components are same with previous projects.
Wind turbine of Figure5 is a wind ground installation. Its peculiarity is a gigantic cableblade
rotor. That has a large power for low ground wind speed. It has four columns with
rollers and closed-loop cable rotor with blades 10. The wind moves the blades, the blades
move the cable, and the cable rotates an electric generator 4.
PROBLEMS OF LAUNCH, START, GUIDANCE, CONTROL,
STABILITY, AND OTHERS
Launching. It is not difficult to launch the installations having support wing or blades as
described in Figure1-4. If the wind speed is more than the minimum required speed (>2-3
m/s), the support wing lifts the installation to the desired altitude.
Starting. All low-speed rotors are self-starting. All high-speed rotors (include the ground
rotor of Figure 5) require an initial starting rotation from the ground motor-generator 4
(figures 1,5).
Guidance and Control. The control of power, revolutions per minute, and torque moment
are operated by the turning of blades around the blade longitudinal axis. The control of
altitude may be manual or automatic when the wind speed is normal and over admissible
minimum. Control is effected by wing flaps and stabilizer (elevator), fin, and ailerons (figs.
1,2,4).
264 Alexander Bolonkin
Stability. Stability of altitude is produced by the length of the cable. Stability around the
blade longitudinal axis is made by stabilizer (see figs.1,2,4). Rotor directional stability in line
with the flow can be provided by fins (figs. 1). When the installation has the support wing
rigidly connected to the rotor, the stability is also attained by the correct location of the center
of gravity of the installation (system rotor-wing) and the point of connection of the main
cable and the tension elements. The center-of-gravity and connection point must be located
within a relatively narrow range 0.2-0.4 of the average aerodynamic chord of the support
wing (for example, see Figure 1). There is the same requirement for the additional support
wings such as Figure2-4.
Figure 1. Propeller high altitude wind energy installation and cable energy transport system. Notation:
a – side view; 1 – wind rotor; 2 – wing with ailerons; 3 – cable energy transport system; 4 – electric
generator; 5 – stabilizer; b – front view; c – side view with a support dirigible 9, vertical cable 6, and
wind speed sensors 7; d - keeping of the installation at a high altitude by rotate propeller; e – three lines
of the transmission - keeper system. That includes: main (central) cable and two mobile transmission
cables; f – energy transport system with variable altitude; 8 – mobile roller.
Figure 2. High altitude wind energy installation with the cable turbine. Notation: 10 – blades; 11 –
tensile elements (bracing)(option).
New Concepts, Ideas and Innovations in Aerospace… 265
Figure 3. High altitude wind energy installation with the parachute turbine.
Figure 4. High altitude wind energy installation with Darrieus turbine.
Figure 5. Ground wind cable rotor of a large power.
Torque moment is balanced by transmission and wing ailerons (see figs.1-4).
The wing lift force, stress of main cable are all regulated automatic by the wing flap or
blade stabilizer.
The location of the installation of Figure 2 at a given point in the atmosphere may be
provided by tension elements shown on Figure 2. These tension elements provide a turning
266 Alexander Bolonkin
capability for the installation of approximately 450
degrees in the direction of flow (see.
Figure 2.).
Minimum wind speed. The required minimum wind-speed for most of the suggested
installation designs is about 2 m/s. The probability of this low wing speed at high altitude is
very small (less 0.001). This minimum may be decreased still further by using the turning
propeller in an autogiro mode. If the wind speed is approximately zero, the rotor can be
supported in the atmosphere by a balloon (dirigible) as is shown on Figure1c or a propeller
rotated by the ground power station as is shown on Figure 1d. The rotor system may also land
on the ground and start again when the wind speed attains the minimum speed for flight.
A Gusty winds. Large pulsations of wind (aerodynamic energy) can be smoothed out by
inertial fly-wheels.
The suggested Method and Installations for utilization of wind energy has following
peculiarities from current conventional methods and installations:
1. Proposed installation allows the collection of energy from a large area – tens and
even hundreds of times more than conventional wind turbines. This is possible
because an expensive tower is not needed to fix our rotor in space. Our installation
allows the use of a rotor with a very large diameter, for example 100-200 meters or
more.
2. The proposed wind installations can be located at high altitude 100 m - 14 km. The
wind speeds are 2-4 times faster and more stable at high altitude compared to ground
surface winds used by the altitude of conventional windmills (10 - 70 meters of
height). In certain geographic areas high altitude wind flows have a continuous or
permanent nature. Since wind power increases at the cube of wind speed, wind rotor
power increases by 27 times when wind speed increases by 3 times.
3. In proposed wind installation the electric generator is located at ground. There are
proposals where electric generator located near a wind rotor and sends electric
current to a ground by electric wares. However, our rotor and power are very large
(see projects below). Proposed installations produce more power by thousands of
times compared to the typical current wind ground installation (see point 1, 2 above).
The electric generator of 20 MW weighs about 100 tons (specific weigh of the
conventional electric generator is about 3 - 10 kg/kW). It is impossible to keep this
weigh by wing at high altitude for wind speed lesser then 150 m/s.
4. One of the main innovations of the given invention is the cable transfer
(transmission) of energy from the wind rotor located at high altitude to the electric
generator located on ground. In proposed Installation it is used a new cable
transmission made from artificial fibers. This transmission has less a weigh in
thousands times then copper electric wires of equal power. The wire having diameter
more 5 mm passes 1-2 ampere/sq.mm. If the electric generator produces 20 MW with
voltage 1000 Volts, the wire cross-section area must be 20,000 mm2
, (wire diameter
is160 mm). The cross-section area of the cable transmission of equal power is only
37 mm2
(cable diameter 6.8 mm2
for cable speed 300 m/s and admissible stress 200
kg/mm2
, see Project 1). The specific weight of copper is 8930 kg/m3
, the specific
weight of artificial fibers is 1800 kg/m3
. If the cable length for altitude 10 km is 25
km the double copper wire weighs 8930 tons (!!), the fiber transmission cable weighs
only 3.33 tons. It means the offered cable transferor energy of equal length is easier
New Concepts, Ideas and Innovations in Aerospace… 267
in 2682 times, then copper wire. The copper wires is very expensive, the artificial
fiber is cheap.
All previous attempts to place the generator near the rotor and connect it to ground by
electric transmission wires were not successful because the generator and wires are heavy.
SOME INFORMATION ABOUT WIND ENERGY
The power of a wind engine strongly depends on the wind speed (to the third power).
Low altitude wind (H = 10 m) has the standard average speed V = 6 m/s. High altitude wind
is powerful and that has another important advantage, it is stable and constant. This is true
practically everywhere.
Wind in the troposphere and stratosphere are powerful and permanent. For example, at an
altitude of 5 km, the average wind speed is about 20 M/s, at an altitude 10 - 12 km the wind
may reach 40 m/s (at latitude of about 20 - 350 N).
There are permanent jet streams at high altitude. For example, at H = 12-13 km and about
250 N latitude. The average wind speed at its core is about 148 km/h (41 m/s). The most
intensive portion, with a maximum speed 185 km/h (51 m/s) latitude 220
, and 151 km/h (42
m/s) at latitude 350
in North America. On a given winter day, speeds in the jet core may
exceed 370 km/h (103 m/s) for a distance of several hundred miles along the direction of the
wind. Lateral wind shears in the direction normal to the jet stream may be 185 km/h per 556
km to right and 185 km/h per 185 km to the left.
The wind speed of V = 40 m/s at an altitude H = 13 km provides 64 times more energy
than surface wind speeds of 6 m/s at an altitude of 10 m.
This is a gigantic renewable and free energy source. (See reference: Science and
Technolody,v.2, p.265).
CABLE TRANSMISSION ENERGY PROBLEM
The primary innovations presented in this paper are locating the rotor at high altitude, and
an energy transfer system using a cable to transfer mechanical energy from the rotor to a
ground power station. The critical factor for this transfer system is the weight of the cable,
and its air drag.
Twenty years ago, the mass and air drag of the required cable would not allow this
proposal to be possible. However, artificial fibers are currently being manufactured, which
have tensile strengths of 3 - 5 times more than steel and densities 4 - 5 times less then steel.
There are also experimental fibers (whiskers) which have tensile strengths 30 - 100 times
more than a steel and densities 2 to 5 times less than steel. For example, in the book [6] p.158
(1989), there is a fiber (whisker) CD, which has a tensile strength of = 8000 kg/mm2
and
density (specific gravity) of = 3.5 g/cm3
. If we use an estimated strength of 3500 kg/mm2
(
= 7
.
1010 N/m2
, = 3500 kg/m3
), then the ratio is / = 0.110-6
or / = 10106
. Although the
described (1989) graphite fibers are strong (/ = 10106
), they are at least still ten times
weaker than theory predicts. A steel fiber has a tensile strength of 5000 MPA (500
268 Alexander Bolonkin
kg/sq.mm), the theoretical limit is 22,000 MPA (2200 kg/mm2
)(1987); the polyethylene fiber
has a tensile strength 20,000 MPA with a theoretical limit of 35,000 MPA (1987). The very
high tensile strength is due to its nanotubes structure.
Apart from unique electronic properties, the mechanical behavior of nanotubes also has
provided interest because nanotubes are seen as the ultimate carbon fiber, which can be used
as reinforcements in advanced composite technology. Early theoretical work and recent
experiments on individual nanotubes (mostly MWNT‘s, Multi Wall Nano Tubes) have
confirmed that nanotubes are one of the stiffest materials ever made. Whereas carbon-carbon
covalent bonds are one of the strongest in nature, a structure based on a perfect arrangement
of these bonds oriented along the axis of nanotubes would produce an exceedingly strong
material. Traditional carbon fibers show high strength and stiffness, but fall far short of the
theoretical, in-plane strength of graphite layers by an order of magnitude. Nanotubes come
close to being the best fiber that can be made from graphite.
For example, whiskers of Carbon nanotube (CNT) material have a tensile strength of 200
Giga-Pascals and a Young‘s modulus over 1 Tera Pascals (1999). The theory predicts 1 Tera
Pascals and a Young‘s modules of 1-5 Tera Pascals. The hollow structure of nanotubes makes
them very light (the specific density varies from 0.8 g/cc for SWNT‘s (Single Wall Nano
Tubes) up to 1.8 g/cc for MWNT‘s, compared to 2.26 g/cc for graphite or 7.8 g/cc for steel).
Specific strength (strength/density) is important in the design of the systems presented in
this paper; nanotubes have values at least 2 orders of magnitude greater than steel. Traditional
carbon fibers have a specific strength 40 times that of steel. Since nanotubes are made of
graphitic carbon, they have good resistance to chemical attack and have high thermal
stability. Oxidation studies have shown that the onset of oxidation shifts by about 1000 C or
higher in nanotubes compared to high modulus graphite fibers. In a vacuum, or reducing
atmosphere, nanotube structures will be stable to any practical service temperature.
The artificial fibers are cheap and widely used in tires and everywhere. The price of SiC
whiskers produced by Carborundum Co. with = 20,690 MPa and = 3.22 g/cc was $440
/kg in 1989. The market price of nanotubes is too high presently (~ $200 per gram)(2000). In
the last 2 - 3 years, there have been several companies that were organized in the US to
produce and market nanotubes. It is anticipated that in the next few years, nanotubes will be
available to consumers for less than $100/pound.
The material property os presented in Part A, Ch.1, Table 2. See also Reference [6]-[9].
Below, the author provides a brief overview of recent research information regarding the
proposed experimental (tested) fibers. In addition, the author also addresses additional
examples, which appear in these projects and which can appear as difficult as the proposed
technology itself. The author is prepared to discuss the problems with organizations which are
interested in research and development related projects.
Industrial fibers with = 500 - 600 kg/mm2
, = -1800 kg/m3
, and = 2,78×106
are
used in all our projects (safety = 200 - 250 kg/mm2
)(see below).
New Concepts, Ideas and Innovations in Aerospace… 269
BRIEF THEORY OF ESTIMATION OF SUGGESTED
INSTALLATIONS
Rotor
Power of a wind energy N [Watt, Joule/sec]
N = 0.5AV3
[W] (1)
The coefficient of efficiency, , equals 0.15-0.35 for low speed rotors (ratio of blade tip
speed to wind speed equals 1); = 0.35-0.5 for high speed rotors ( = 5-7). The Darrieus
rotor has = 0.35-0.4. The propeller rotor has = 0.45-0.50. The theoretical maximum
equals = 0.67.
The energy is produced in one year is (1 year 30.2106 work sec) [J]
E = 360024350N 30106N [J]. (1‘)
Wind speed increases with altitude as follows
V=(H/Ho)
Vo , (2)
where = 0.1 - 0.25 exponent coefficient depends from surface roughness. When the surface
is water, = 0.1; when surface is shrubs and woodlands = 0.25.
Power increases with altitude as the cube of wind speed
N = (H/Ho)
3No , (3)
where No is power at Ho.
The drag of the rotor equals
Dr= N/V (4)
The lift force of the wing, Ly
, is
Ly = 0.5CLV
2
Aw , Ly W , (5)
where CL is lift coefficient (maximum CL 2.5), Aw is area of the wing, W is weight of
installation + 0.5 weight of all cables.
The drag of the wing is
D = 0.5CDV
2
Aw , (6)
where CD is the drag coefficient (maximum CD 1.2).
270 Alexander Bolonkin
The optimal speed of the parachute rotor equals 1/3V and the theoretical maximum of
efficiency coefficient is 0.5.
The annual energy produced by the wind energy extraction installation equals
E = 8.33N [kWh] (7)
Cable Energy Transfer, Wing Area, and other Parameters
Cross-section area of transmission cable, S , is
S=N/v , (8)
Cross-section area of main cable, Sm , is
Sm=(Dr+D)/ , (8‘)
Weight of cable is
Wr=SL , (9)
The production cost, c, in kWh is
E
M I K
c
1 /
,
(10)
The annual profit
F= (C-c)E . (11)
The required area of the support wing is
L
w
C
A
A
sin
(12)
where is the angle between the support cable and horizontal surface.
The wing area is served by ailerons for balancing of the rotor (propeller) torque moment
C r
AR A
i L a
a
,
(13)
The minimum wind speed for installation support by the wing alone
New Concepts, Ideas and Innovations in Aerospace… 271
CL Aw
W
V
,max
min
2
(14)
where W is the total weight of the airborne system including transmission. If a propeller rotor
is used in a gyroplane mode, minimal speed will decrease by 2-2,5 times. If wind speed
equals zero, the required power for driving the propeller in a propulsion (helicopter) mode is
Ns = W/K2 [kW], (15)
The specific weight of energy storage (flywheel) can be estimated by
Es=/2 [J/kg]. (16)
For example, if =200 kg/mm2
, =1800 kg/m3
, then Es = 0.56 MJ/kg or Es = 0.15
kWh/kg.
For comparison of the different ground wind installations their efficiency and parameters
are computed for the standard wind conditions: the wind speed equals V = 6 m/s at the
altitude H = 10 m.
PROJECTS
Project 1
High-Speed Air Propeller Rotor (Figure 1)
For example, let us consider a rotor diameter of 100 m (A = 7850 m2
), at an altitude H =
10 km ( = 0.4135 kg/m3
), wind speed of V = 30 m/s , an efficiency coefficient of = 0.5,
and a cable tensile stress of = 200 kg/mm2
.
Then the power produced is N = 22 MW [Eq. (1)], which is sufficient for city with a
population of 250,000. The rotor drag is Dr = 73 tons [Eq.(4)], the cross-section of the main
cable area is S =1.4Dr
/σ = l.3573/0.2 500 mm2
, the cable diameter equals d = 25 mm; and
the cable weight is W = 22.5 tons [Eq.(9)] (for L = 25 km). The cross-section of the
transmission cable is S = 36.5 mm2
[Eq.(8)], d = 6.8 mm, weight of two transmission cables is
W = 3.33 tons for cable speed v = 300 m/s [Eq.(9)].
The required wing size is 20100 m (CL=0.8) [Eq.(12)], wing area served by ailerons is
820 m
2
[Eq.(13)]. If CL = 2, the minimum speed is 2 m/s [Eq.(14)].
The installation will produce an annual energy E = 190 GWh [Eq.(7)]. If the installation
cost is $200K, has a useful life of 10 years, and requires maintenance of $50K per year, the
production cost is c = 0.37 cent per kWh [Eq(10)]. If retail price is $0.15 per kWh, profit $0.1
per kWh, the total annual profit is $19 millions per year [Eq.(11)].
The Project #2
Large Air Propeller at Altitude H = 1 km (Figure 1)
272 Alexander Bolonkin
Let us consider a propeller diameter of 300 m, with an area A = 7104
m
2
, at an altitude H
= 1 km, and a wind speed of 13 m/s. The average blade tip speed is 78 m/s.
The full potential power of the wind streamer flow is 94.2 MW. If the coefficient of
efficiency is 0.5 the useful power is N = 47.1 MW. For other wind speed. the useful power is:
V = 5 m/s, N = 23.3 MW; V = 6 m/s, N = 47.1 MW; V = 7 m/s, N = 74.9 MW; V = 8 m/s, N =
111.6 MW; V = 9 m/s, N = 159 MW; V = 10 m/s, N =218 MW.
Estimation of Economical Efficiency
Let us assume that the cost of the Installation is $3 million, a useful life of 10 years, and
request maintenance of $100,000/year. The energy produced in one year is E = 407 GWh
[Eq.(7)]. The basic cost of energy is $0.01 /kWh.
The Some Technical Parameters
Altitude H = 1 km
The drag is about 360 tons. Ground connection (main) cable has cross-section area of
1800 sq.mm [Eq.(8‘)], d = 48 mm, and has a weight of 6480 kg. The need wing area is
60x300 m. The aileron area requested for turbine balance is 6740 sq.m.
If the transmission cable speed is 300 m/s, the cross-section area of transmission cable is
76 sq.mm and the cable weight is 684 kg (composite fiber).
Altitude H = 13 km
At an altitude of H =13 km. the air density is ρ = 0.2666, and the wind speed is V = 40
m/s. The power for efficiency coefficient 0.5 is 301.4 MgW. The drag of the propeller is
approximately 754 tons. The connection cable has a cross-sectional area of 3770 sq.mm, a
diameter is d =70 mm and a weight of 176 tons. The transmission cable has a sectional area 5
sq.cm and a weight of 60 tons (vertical transmission only 12 tons).
The installation will produce energy E = 2604 GWh per year. If the installation costs $5
million, maintenance is $200,000/year, and the cost of 1 kWh will be $0.0097/kWh.
Project #3
Air Low Speed Wind Engine with Free Flying Cable Flexible Rotor (Figure 2)
Let us consider the size of cable rotor of width 50 m, a rotor diameter of 1000 m, then the
rotor area is A =501000 = 50,000 sq.m. The angle rope to a horizon is 70o
. The angle of ratio
lift/drag is about 2.5o
.
The average conventional wind speed at an altitude H = 10 m is V = 6 m/s. It means that
the speed at the altitude 1000 m is 11.4 - 15 m/s. Let us take average wind speed V = 13 m/s
at an altitude H = 1 km.
The power of flow is
N = 0.5.
V
3
A cos 200= 0.51.225133
1000500.94 = 63 MW.
If the coefficient efficiency is = 0.2 the power of installation is
New Concepts, Ideas and Innovations in Aerospace… 273
P =N = 0.263 = 12.5 MW.
The energy 12.5 MW is enough for a city with a population at 150,000.
If we decrease our Installation to a 100×2000 m the power decreases approximately by 6
times (because the area decreases by 4 times, wind speed reaches more 15 m/s at this altitude.
Power will be 75 MW. This is enough for a city with a population about 1 million of people.
If the average wind speed is different for given location the power for the basis
installation will be: V = 5 m/s, N =7.25 MW; V = 6 m/s, N = 12.5 MW; V = 7 m/s, N = 19.9
MW; V = 8 m/s, N = 29,6 MW; V = 9 m/s, N = 42.2 MW; V = 10 m/s, N = 57.9 MW.
Economical Efficiency
Let us assume that the cost of our installation is $1 million. According to the book ―Wind
Power‖ by P. Gipe [2], the conventional wind installation with the rotor diameter 7 m costs
$20,000 and for average wind speeds of 6 m/s has power 2.28 kW, producing 20,000 kWh per
year. To produce the same amount of power as our installation using by conventional
methods, we would need 5482 (12500/2.28) conventional rotors, costing $110 million. Let us
assume that our installation has a useful life of 10 years and a maintenance cost is
$50,000/year. Our installation produces 109,500,000 kWh energy per year. Production costs
of energy will be approximately 150,000/109,500,000 = 0.14 cent/kWh. The retail price of 1
kWh of energy in New York City is $0.15 now. The revenue is 16 millions. If profit from 1
kWh is $0.1, the total profit is more 10 millions per year.
Estimation Some Technical Parameters
The cross-section of main cable for an admissible fiber tensile strange = 200kg/sq.mm
is S =2000/0.2 = 10,000 mm2
. That is two cable of diameter d =80 mm. The weight of the
cable for density 1800 kg/m3
is
W = SL = 0.01
.
2000
.
1800 = 36 tons.
Let us assume that the weight of 1 sq.m of blade is 0.2 kg/m2
and the weight of 1 m of
bulk is 2 kg. The weight of the 1 blade will be 0.2 x 500 = 100 kg, and 200 blades are 20 tons.
If the weight of one bulk is 0.1 ton, the weight of 200 bulks is 20 tons.
The total weight of main parts of the installation will be 94 tons. We assume 100 tons for
purposes of our calculations.
The minimum wind speed when the flying rotor can supported in the air is (for Cy = 2)
V=(2W/CyS)0.5=(2100104
/21.225200500)0.5 = 2.86 m/s
The probability of the wind speed falling below 3 m/s when the average speed is 12 m/s,
is zero, and for 10 m/s is 0.0003. This equals 2.5 hours in one year, or less than one time per
year. The wind at high altitude has greater speed and stability than near ground surface. There
is a strong wind at high altitude even when wind near the ground is absent. This can be seen
when the clouds move in a sky on a calm day.
274 Alexander Bolonkin
Project #4
Low Speed Air Drag Rotor (Figure 3)
Let us consider a parachute with a diameter of 100 m, length of rope 1500 m, distance
between the parachutes 300 m, number of parachute 3000/300 = 10, number of worked
parachute 5, the area of one parachute is 7850 sq.m, the total work area is A = 5 ×7850 = 3925
sq.m. The full power of the flow is 5.3 MW for V=6 m/s. If coefficient of efficiency is 0.2 the
useful power is N = 1 MW. For other wind speed the useful power is: V = 5 m/s, N =0.58
MW; V =6 m/s, N = 1 MW; V =7 m/s, N =1.59 MW; V = 8 m/s, N=2.37 MW; V = 9 m/s, N
=3.375 MW; V = 10 m/s, N = 4.63 MW.
Estimation of Economical Efficiency
Let us take the cost of the installation $0.5 million, a useful life of 10 years and
maintenance of $20,000/year. The energy produced in one year (when the wind has standard
speed 6 m/s) is E = 1000x24x360 = 8.64 million kWh. The basic cost of energy is
70,000/8640,000 = 0.81 cent/kWh.
The Some Technical Parameters
If the thrust is 23 tons, the tensile stress is 200 kg/sq.mm (composed fiber), then the
parachute cable diameter is 12 mm. The full weight of the installation is 4.5 tons. The support
wing has size 25×4 m.
Project #5
High Speed Air Darreus Rotor at an Altitude 1 km (Figure 4)
Let us consider a rotor having the diameter of 100 m, a length of 200 m (work area is
20,000 m2
). When the wind speed at an altitude H = 10 m is V = 6 m/s, then at an altitude H =
1000 m it is 13 m/s. The full wind power is 13,46 MW. Let us take the efficiency coefficient
0.35, then the power of the Installation will be N = 4.7 MW. The change of power from wind
speed is: V = 5 m/s, N = 2.73 MW; V = 6 m/s, N = 4.7 MW; V = 7 m/s, N = 7.5 MW; V = 8
m/s, N = 11.4 MW; V = 9m/s, N = 15.9 MW; V = 10 m/s, N = 21.8 MW.
At an altitude of H = 13 km with an air density 0.267 and wind speed V = 40 m/s, the
given installation will produce power N = 300 MW.
Estimation of Economical Efficiency
Let us take the cost of the Installation at $1 million, a useful life of 10 years, and
maintenance of $50,000 /year. Our installation will produce E = 41 millions kWh per year
(when the wind speed equals 6 m/s at an altitude 10 m). The prime cost will be
150,000/41,000,000 = 0.37 cent/kWh. If the customer price is $0.15/kWh and profit from 1
kWh is $0.10 /kWh the profit will be $4.1 million per year.
New Concepts, Ideas and Innovations in Aerospace… 275
Estimation of Technical Parameters
The blade speed is 78 m/s. Numbers of blade is 4. Number of revolution is 0.25
revolutions per second. The size of blade is 200x0.67 m. The weight of 1 blade is 1.34 tons.
The total weight of the Installation is about 8 tons. The internal wing has size 200×2.3 m. The
additional wing has size 200x14.5 m and weight 870 kg. The cross-section area of the cable
transmission having an altitude of H = 1 km is 300 sq.mm, the weight is 1350 kg.
Project #6
Ground Wind High Speed Engine (Figure 5)
Let us consider the ground wind installation (Figure5) with size 500×500×50 meters. The
work area is 500×50×2 = 50,000 sq.m. The tower is 60 meter tall, the flexible rotor located
from 10 m to 60 m. If the wind speed at altitude 10 m is 6 m/s, that equals 7.3 m/s at altitude
40 m.
The theoretical power is
Nt = 0.5 V
3
A = 0.51.2257.33
5104
= 11.9 MgW.
For coefficient of the efficiency equals 0.45 the useful power is
N = 0.4511.9 = 5.36 MW.
For other wind speed at an altitude 6 m/s the useful power is: V = 5 m/s, N = 3.1 MW; V
= 6 m/s, N = 5.36 MW; V = 7 m/s, N = 8.52 MW; V = 8 m/s, N = 12.7 MW; V = 9 m/s, N =
18.1 MW; V = 10 m/s, N = 24.8 MW.
Economic Estimation
In this installation the rotor will be less expensive than previous installations because the
high-speed rotor has a smaller number of blades and smaller blades (see technical data
below). However this installation needs 4 high (60 m) columns. Take the cost of the
installation at $1 million with a useful life of 10 years. The maintenance is projected at about
$50,000 /year.
This installation will produce E = 5360 kW × 8760 hours = 46.95 MWh energy (for the
annual average wind-speed V = 6 m/s at H = 10 m). The cost of 1 kWh is 150,000/46,950,000
= 0.4 cent/kWh. If the retail price is $0.15/kWh and delivery cost 30%, the profit is $0.10 per
kWh, or $4.7 million per year.
Estimation of Some Technical Parameters
The blade speed is 6 × 7.3 = 44 m/s. The distance between blades is 44 m. The number of
blade is 4000/44 = 92.
276 Alexander Bolonkin
DISCUSSION AND CONCLUSION
Conventional windmills are approached their maximum energy extraction potential
relative to their installation cost. No relatively progress has been made in windmill
technology in the last 50 years. The wind energy is free, but its production more expensive
then its production in heat electric stations. Current wind installations cannot essential
decrease a cost of kWh, stability of energy production. They cannot increase of power of
single energy unit. The renewable energy industry needs revolutionary ideas that improve
performance parameters (installation cost and power per unit) and that significantly decreases
(in 10-20 times) the cost of energy production. This paper offers ideas that can move the wind
energy industry from stagnation to revolutionary potential.
The following is a list of benefits provided by the proposed system compared to current
installations:
1. The produced energy at least in 10 times cheaper then energy received of all
conventional electric stations includes current wind installation.
2. The proposed system is relatively inexpensive (no expensive tower), it can be made
with a very large thus capturing wind energy from an enormous area (hundreds of
times more than typical wind turbines).
3. The power per unit of proposed system in some hundreds times more of typical
current wind installations.
4. The proposed installation not requires large ground space.
5. The installation may be located near customers and not require expensive high
voltage equipment. It is not necessary to have long, expensive, high-voltage
transmission lines and substations. Ocean going vessels can use this installation for
its primary propulsion source.
6. No noise and bad views.
7. The energy production is more stability because the wind is steadier at high altitude.
The wind may be zero near the surface but it is typically strong and steady at higher
altitudes. This can be observed when it is calm on the ground, but clouds are moving
in the sky. There are a strong permanent air streams at a high altitude at many
regions of the USA.
8. The installation can be easy relocated in other place.
As with any new idea, the suggested concept is in need of research and development. The
theoretical problems do not require fundamental breakthroughs. It is necessary to design
small, free flying installations to study and get an experience in the design, launch, stability,
and the cable energy transmission from a flying wind turbine to a ground electric generator.
This paper has suggested some design solutions from patent application [4]. The author
has many detailed analysis in addition to these presented projects. Organizations interested in
these projects can address the author (http://Bolonkin.narod.ru , aBolonkin@juno.com ,
abolonkin@gmail.com). The other ideas are in [11]-[50].
New Concepts, Ideas and Innovations in Aerospace… 277
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: Bolonkin, and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Bolonkin A.A., Utilization of Wind Energy at High Altitude, AIAA-2004-5756, AIAA2004-5705.
International Energy Conversion Engineering Conference at Providence,
RI, USA, Aug.16-19, 2004.
[2] Gipe P., Wind Power, Chelsea Green Publishing Co., Vermont, 1998.
[3] Thresher R.W. and etc, Wind Technology Development: Large and Small Turbines,
NRFL, 1999.
[4] Bolonkin, A.A., ‖Method of Utilization a Flow Energy and Power Installation for It‖,
USA patent application 09/946,497 of 09/06/2001.
[5] Bolonkin, A.A., Transmission Mechanical Energy to Long Distance. AIAA-2004-5660.
[6] Galasso F.S., Advanced Fibers and Composite, Gordon and Branch Scientific
Publisher, 1989.
[7] Carbon and High Performance Fibers Directory and Data Book, London-New. York:
Chapmenand Hall, 1995, 6th ed., 385 p.
[8] Concise Encyclopedia of Polymer Science and Engineering, Ed. J.I.Kroschwitz, N.
Y.,Wiley, 1990, 1341 p.
[9] Dresselhaus, M.S., Carbon Nanotubes, by, Springer, 2000.
[10] Bolonkin, A.A., ―Inexpensive Cable Space Launcher of High Capability‖, IAC-02-
V.P.07, 53rd International Astronautical Congress. The World Space Congress – 2002,
10-19 Oct. 2002/Houston, Texas, USA. JBIS, Vol.56, pp.394-404, 2003.
[11] Bolonkin, A.A, ―Non-Rocket Missile Rope Launcher‖, IAC-02-IAA.S.P.14, 53rd
International Astronautical Congress. The World Space Congress – 2002, 10-19 Oct
2002/Houston, Texas, USA. JBIS, Vol.56, pp.394-404, 2003.
[12] Bolonkin, A.A., ―Hypersonic Launch System of Capability up 500 tons per day and
Delivery Cost $1 per Lb‖. IAC-02-S.P.15, 53rd International Astronautical Congress.
The World Space Congress – 2002, 10-19 Oct 2002/Houston, Texas, USA. JBIS,
Vol.57, pp.162-172. 2004.
[13] Bolonkin, A.A., ―Employment Asteroids for Movement of Space Ship and Probes‖.
IAC-02-S.6.04, 53rd International Astronautical Congress. The World Space Congress –
2002, 10-19 Oct. 2002/Houston, USA. JBIS, Vol.56, pp.98-197, 2003.
[14] Bolonkin, A.A., ―Non-Rocket Space Rope Launcher for People‖, IAC-02-V.P.06, 53rd
International Astronautical Congress. The World Space Congress – 2002, 10-19 Oct
2002/Houston, Texas, USA. JBIS, Vol.56, pp.231-249, 2003.
[15] Bolonkin, A.A., ―Optimal Inflatable Space Towers of High Height‖. COSPAR-02 C1.1-
0035-02, 34th Scientific Assembly of the Committee on Space Research (COSPAR).
The World Space Congress – 2002, 10-19 Oct 2002/Houston, Texas, USA. JBIS,
Vol.56, pp.87-97, 2003.
[16] Bolonkin, A.A., ―Non-Rocket Earth-Moon Transport System‖, COSPAR-02 B0.3-F3.3-
0032-02, 34th Scientific Assembly of the Committee on Space Research (COSPAR).
278 Alexander Bolonkin
The World Space Congress – 2002, 10-19 Oct 2002, Houston, Texas, USA. ―Advanced
Space Research”, Vol.31, No. 11, pp. 2485-2490, 2003.
[17] Bolonkin, A.A., ―Non-Rocket Earth-Mars Transport System‖, COSPAR-02B0.4-C3.4-
0036-02, 34th Scientific Assembly of the Committee on Space Research (COSPAR).
The World Space Congress – 2002, 10-19 Oct 2002/Houston, Texas, USA. Actual
problems of aviation and space system. No.1(15), vol.8, pp.63-73, 2003.
[18] Bolonkin, A.A., ―Transport System for delivery Tourists at Altitude 140 km‖. IAC-02-
IAA.1.3.03, 53rd International Astronautical Congress. The World Space Congress –
2002, 10-19 Oct. 2002/Houston, Texas, USA. JBIS, Vol.56, pp.314-327, 2003.
[19] Bolonkin, A.A., ‖Hypersonic Gas-Rocket Launch System.‖, AIAA-2002-3927, 38th
AIAA/ASME/SAE/ ASEE Joint Propulsion Conference and Exhibit, 7-10 July, 2002.
Indianapolis, IN, USA.
[20] Bolonkin, A.A., Multi-Reflex Propulsion Systems for Space and Air Vehicles and
Energy Transfer for Long Distance, JBIS, Vol, 57, pp.379-390, 2004.
[21] Bolonkin A.A., Electrostatic Solar Wind Propulsion System, AIAA-2005-3653. 41
Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[22] Bolonkin A.A., Electrostatic Utilization of Asteroids for Space Flight, AIAA-2005-
4032. 41 Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[23] Bolonkin A.A., Kinetic Anti-Gravitator, AIAA-2005-4504. 41 Propulsion Conference,
10-12 July, 2005, Tucson, Arizona, USA.
[24] Bolonkin A.A., Sling Rotary Space Launcher, AIAA-2005-4035. 41 Propulsion
Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[25] Bolonkin A.A., Radioisotope Space Sail and Electric Generator, AIAA-2005-4225. 41
Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[26] Bolonkin A.A., Guided Solar Sail and Electric Generator, AIAA-2005-3857. 41
Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[27] Bolonkin A.A., Problems of Electrostatic Levitation and Artificial Gravity, AIAA2005-4465.
41 Propulsion Conference, 10-12 July, 2005, Tucson, Arizona, USA.
[28] A.A. Bolonkin, Space Propulsion using Solar Wing and Installation for It. Russian
patent application #3635955/23 126453, 19 August, 1983 (in Russian). Russian PTO.
[29] A, Bolonkin, Installation for Open Electrostatic Field. Russian patent application
#3467270/21 116676, 9 July, 1982 (in Russian). Russian PTO.
[30] A.A.Bolonkin, Getting of Electric Energy from Space and Installation for It. Russian
patent application #3638699/25 126303, 19 August, 1983 (in Russian). Russian PTO.
[31] A.A.Bolonkin, Protection from Charged Particles in Space and Installation for It.
Russian patent application #3644168 136270 of 23 September 1983, (in Russian).
Russian PTO.
[32] A.A.Bolonkin, Method of Transformation of Plasma Energy in Electric Current and
Installation for It. Russian patent application #3647344 136681 of 27 July 1983 (in
Russian), Russian PTO.
[33] A.A.Bolonkin, Method of Propulsion using Radioisotope Energy and Installation for It.
of Plasma Energy in Electric Current and Installation for it. Russian patent application
#3601164/25 086973 of 6 June, 1983 (in Russian), Russian PTO.
[34] A.A.Bolonkin, Transformation of Energy of Rarefaction Plasma in Electric Current
and Installation for it. Russian patent application #3663911/25 159775 of 23 November
1983 (in Russian). Russian PTO.
New Concepts, Ideas and Innovations in Aerospace… 279
[35] A.A.Bolonkin, Method of a Keeping of a Neutral Plasma and Installation for it.
Russian patent application #3600272/25 086993 of 6 june 1983 (in Russian). Russian
PTO.
[36] A.A.Bolonkin, Radioisotope Propulsion. Russian patent application #3467762/25
116952 of 9 July 1982 (in Russian). Russian PTO.
[37] A.A.Bolonkin, Radioisotope Electric Generator. Russian patent application
#3469511/25 116927 of 9 July 1982 (in Russian). Russian PTO.
[38] A.A.Bolonkin, Radioisotope Electric Generator. Russian patent application
#3620051/25 108943 of 13 July 1983 (in Russian). Russian PTO.
[39] A.A.Bolonkin, Method of Energy Transformation of Radioisotope Matter in Electricity
and Installation for it. Russian patent application #3647343/25 136692 of 27 July 1983
(in Russian). Russian PTO.
[40] A.A.Bolonkin, Method of stretching of thin film. Russian patent application
#3646689/10 138085 of 28 September 1983 (in Russian). Russian PTO.
[41] Bolonkin, A.A. and R.B. Cathcart, Inflatable ‗Evergreen‘ Dome Settlements for Earth‘s
Polar Regions. Clean. Techn. Environ. Policy. DOI 10.1007/s10098.006-0073.4 .
[42] Bolonkin, A.A. and R.B. Cathcart, ―A Cable Space Transportation System at the
Earth‘s Poles to Support Exploitation of the Moon‖, Journal of the British
Interplanetary Society 59: 375-380, 2006.
[43] Bolonkin A.A., Cheap Textile Dam Protection of Seaport Cities against Hurricane
Storm Surge Waves, Tsunamis, and Other Weather-Related Floods, 2006.
http://arxiv.org.
[44] Bolonkin, A.A. and R.B. Cathcart, Antarctica: A Southern Hemisphere Windpower
Station? Arxiv, 2007.
[45] Bolonkin A.A., Cathcart R.B., Inflatable ‗Evergreen‘ Polar Zone Dome (EPZD)
Settlements, 2006. http://arxiv.org
[46] Bolonkin, A.A. and R.B. Cathcart, The Java-Sumatra Aerial Mega-Tramway, 2006.
http://arxiv.org.
[47] Bolonkin, A.A., ―Optimal Inflatable Space Towers with 3-100 km Height‖, Journal of
the British Interplanetary Society Vol. 56, pp. 87 - 97, 2003.
[48] Bolonkin A.A., Non-Rocket Space Launch and Flight, Elsevier, London, 2006, 488 pgs.
[49] Macro-Engineering: A Challenge for the Future. Springer, 2006. 318 pgs. Collection of
articles.
[50] Cathcart R.B. and Bolonkin, A.A. Ocean Terracing, 2006. http://arxiv.org.
280 Alexander Bolonkin
Attacment to Part B, Ch. 2.
Possible fly wind engine
Ground wind energy instellations
New Concepts, Ideas and Innovations in Aerospace…
Chapter 3
CONTROL OF REGIONAL AND GLOBAL
EARTH WEATHER
ABSTRACT
Author suggests and researches a new revolutionary idea for regional and global
weather control. He offers to cover cities, bad regions of country, full country or a
continent by a thin closed film with control clarity located at a top limit of the Earth's
troposphere (4 - 6 km). The film is supported at altitude by small additional atmospheric
pressure and connected to ground by thin cables. It is known, the troposphere defines the
Earth's weather. Authors show this closed dome allows to do a full control of the weather
in a given region (the day is always fine, the rain is only in night, no strong wind). The
average Earth (white cloudy) reflectance equal 0.3 - 0.5. That means the Earth losses
about 0.3 - 0.5 of a solar energy. The dome controls the clarity of film and converts the
cold regions to subtropics and creates the hot deserts, desolate wildernesses to the
prosperous regions with temperate climate. That is a realistic and the cheapest method of
the weather control in the Earth at the current time.
Keywords: Global weather control, gigantic film dome, converting a cold region to
subtropics, converting desolate wilderness to a prosperous region.
INTRODUCTION
Governments spend billions of dollars to studying of weather. The many big
government research scientific organizations and hundred thousands of scientists studying a
Earth weather more then hundred years. There are gigantic numbers of scientific works about
weather control. Most of them are out of practice. We cannot exactly predict weather at long
period, to avert a rain, strong wind, storm, hurricane, tornado. We cannot control the clouds,
temperature and humidity of atmosphere, power of rain. We cannot make better a winter and
summer. We cannot convert a cold region to subtropics, a desolate wilderness to a prosperous
region. We can only observe the storms and hurricanes and approximately predict their
Kept in http://arxiv.org , 2006.
282 Alexander Bolonkin
direction of movement. Every year the terrible storms, hurricanes, strong winds and rains,
inundations destroy thousands of houses, kill thousands of men.
In this chapter, we consider a damage and prejudice from unnormal weather.
1. A tropical cyclone (hurricane) is a storm system fueled by the heat released when
moist air rises and the water vapor in it condenses. The term describes the storm's origin in
the tropics and its cyclonic nature, which means that its circulation is counterclockwise in
the northern hemisphere and clockwise in the southern hemisphere. Tropical cyclones are
distinguished from other cyclonic windstorms such as nor'easters, European windstorms,
and polar lows by the heat mechanism that fuels them, which makes them "warm core" storm
systems.
Depending on their location and strength, there are various terms by which tropical
cyclones are known, such as hurricane, typhoon, tropical storm, cyclonic storm and tropical
depression.
Tropical cyclones can produce extremely strong winds, tornadoes, torrential rain, high
waves, and storm surges. The heavy rains and storm surges can produce extensive flooding.
Although their effects on human populations can be devastating, tropical cyclones also can
have beneficial effects by relieving drought conditions. They carry heat away from the
tropics, an important mechanism of the global atmospheric circulation that maintains
equilibrium in the earth's troposphere.
An average of 86 tropical cyclones of tropical storm intensity form annually worldwide,
with 47 reaching hurricane/typhoon strength, and 20 becoming intense tropical cyclones (at
least of Category 3 intensity).
Worldwide, tropical cyclone activity peaks in late summer when water temperatures are
warmest. However, each particular basin has its own seasonal patterns. On a worldwide scale,
May is the least active month, while September is the most active.
Table 1. Season Lengths and Seasonal Averages
Basin Season
Start Season End
Tropical
Storms
(>34 knots)
Tropical
Cyclones
(>63 knots)
Category 3+
Tropical
Cyclones
(>95 knots)
Northwest Pacific – – 26.7 16.9 8.5
South Indian October May 20.6 10.3 4.3
Northeast Pacific May November 16.3 9.0 4.1
North Atlantic June November 10.6 5.9 2.0
Australia
Southwest Pacific October May 10.6 4.8 1.9
North Indian April December 5.4 2.2 0.4
In the North Atlantic, a distinct hurricane season occurs from June 1 to November 30,
sharply peaking from late August through September. The statistical peak of the North
Atlantic hurricane season is September 10. The Northeast Pacific has a broader period of
New Concepts, Ideas and Innovations in Aerospace… 283
activity, but in a similar time frame to the Atlantic. The Northwest Pacific sees tropical
cyclones year-round, with a minimum in February and a peak in early September. In the
North Indian basin, storms are most common from April to December, with peaks in May and
November.
A mature tropical cyclone can release heat at a rate upwards of 6x1014 watts. Tropical
cyclones on the open sea cause large waves, heavy rain, and high winds, disrupting
international shipping and sometimes sinking ships. However, the most devastating effects of
a tropical cyclone occur when they cross coastlines, making landfall. A tropical cyclone
moving over land can do direct damage in four ways:
• High winds - Hurricane strength winds can damage or destroy vehicles, buildings,
bridges, etc. High winds also turn loose debris into flying projectiles, making the
outdoor environment even more dangerous.
• Storm surge - Tropical cyclones cause an increase in sea level, which can flood
coastal communities. This is the worst effect, as historically cyclones claimed 80% of
their victims when they first strike shore.
• Heavy rain - The thunderstorm activity in a tropical cyclone causes intense rainfall.
Rivers and streams flood, roads become impassable, and landslides can occur. Inland
areas are particularly vulnerable to freshwater flooding, due to residents not
preparing adequately.
• Tornado activity - The broad rotation of a hurricane often spawns tornadoes. Also,
tornadoes can be spawned as a result of eyewall mesovortices, which persist until
landfall. While these tornadoes are normally not as strong as their non-tropical
counterparts, they can still cause tremendous damage.[31]
Figure 1. The aftermath of Hurricane Katrina in Gulfport, Mississippi. Katrina was the costliest tropical
cyclone in United States history.
Often, the secondary effects of a tropical cyclone are equally damaging. These include:
Disease - The wet environment in the aftermath of a tropical cyclone, combined with the
destruction of sanitation facilities and a warm tropical climate, can induce epidemics of
284 Alexander Bolonkin
disease which claim lives long after the storm passes. One of the most common posthurricane
injuries is stepping on a nail in storm debris, leading to a risk of tetanus or other
infection. Infections of cuts and bruises can be greatly amplified by wading in sewagepolluted
water. Large areas of standing water caused by flooding also contribute to mosquitoborne
illnesses.
Power outages - Tropical cyclones often knock out power to tens or hundreds of
thousands of people (or occasionally millions if a large urban area is affected), prohibiting
vital communication and hampering rescue efforts.
Transportation difficulties - Tropical cyclones often destroy key bridges, overpasses, and
roads, complicating efforts to transport food, clean water, and medicine to the areas that need
it.
Hurricane Katrina is the most obvious example, as it devastated the region that had been
revitalized after Hurricane Camille. Of course, many former residents and businesses do
relocate to inland areas away from the threat of future hurricanes as well.
While the number of storms in the Atlantic has increased since 1995, there seems to be
no signs of a numerical global trend; the annual global number of tropical cyclones remains
about 90 ± 10. However, there is some evidence that the intensity of hurricanes is increasing.
"Records of hurricane activity worldwide show an upswing of both the maximum wind speed
in and the duration of hurricanes. The energy released by the average hurricane (again
considering all hurricanes worldwide) seems to have increased by around 70% in the past 30
years or so, corresponding to about a 15% increase in the maximum wind speed and a 60%
increase in storm lifetime."
Atlantic storms are certainly becoming more destructive financially, since five of the ten
most expensive storms in United States history have occurred since 1990. This can be
attributed to the increased intensity and duration of hurricanes striking North America and to
the number of people living in susceptible coastal area following increased development in
the region since the last surge in Atlantic hurricane activity in the 1960s.
Tropical cyclones that cause massive destruction are fortunately rare, but when they
happen, they can cause damage in the range of billions of dollars and disrupt or end thousands
of lives.
The deadliest tropical cyclone on record hit the densely populated Ganges Delta region of
Bangladesh on November 13, 1970, likely as a Category 3 tropical cyclone. It killed an
estimated 500,000 people. The North Indian basin has historically been the deadliest, with
several storms since 1900 killing over 100,000 people, each in Bangladesh.
In the Atlantic basin, at least three storms have killed more than 10,000 people. Hurricane
Mitch during the 1998 Atlantic hurricane season caused severe flooding and mudslides in
Honduras, killing about 18,000 people and changing the landscape enough that entirely new
maps of the country were needed. The Galveston Hurricane of 1900, which made landfall at
Galveston, Texas as an estimated Category 4 storm, killed 8,000 to 12,000 people, and
remains the deadliest natural disaster in the history of the United States. The deadliest
Atlantic storm on record was the Great Hurricane of 1780, which killed about 22,000 people
in the Antilles.
Hurricane Iniki in 1992 was the most powerful storm to strike Hawaii in recorded history,
hitting Kauai as a Category 4 hurricane, killing six and causing $3 billion in damage. Other
destructive Pacific hurricanes include Pauline and Kenna.
New Concepts, Ideas and Innovations in Aerospace… 285
On March 26, 2004, Cyclone Catarina became the first recorded South Atlantic cyclone
(cyclone is the southern hemispheric term for hurricane). Previous South Atlantic cyclones in
1991 and 2004 reached only tropical storm strength. Tropical cyclones may have formed
there before 1960 but were not observed until weather satellites began monitoring the Earth's
oceans in that year.
A tropical cyclone need not be particularly strong to cause memorable damage; Tropical
Storm Thelma, in November 1991 killed thousands in the Philippines even though it never
became a typhoon; the damage from Thelma was mostly due to flooding, not winds or storm
surge. In 1982, the unnamed tropical depression that eventually became Hurricane Paul
caused the deaths of around 1,000 people in Central America due to the effects of its rainfall.
In addition, Hurricane Jeanne in 2004 caused the majority of its damage in Haiti, including
approximately 3,000 deaths, while just a tropical depression.
On August 29, 2005, Hurricane Katrina made landfall in Louisiana and Mississippi. The
U.S. National Hurricane Center, in its August review of the tropical storm season stated that
Katrina was probably the worst natural disaster in U.S. history. Currently, its death toll is at
least 1,836, mainly from flooding and the aftermath in New Orleans, Louisiana and the
Mississippi Gulf Coast. It is also estimated to have caused $81.2 billion in property damage.
Before Katrina, the costliest system in monetary terms had been 1992's Hurricane Andrew,
which caused an estimated $39 billion (2005 USD) in damage in Florida.
2. A flood (inundation) is an overflow of water, an expanse of water submerging land, a
deluge. In the sense of "flowing water", the word is applied to the inflow of the tide, as
opposed to the outflow or "ebb". The Flood, the great Universal Deluge of myth and perhaps
of history is treated at Deluge in mythology.
Since prehistoric times people have lived by the seas and rivers for the access to cheap
and quick transportation and access to food sources and trade; without human populations
near natural bodies of water, there would be no concern for floods. However fertile soil in a
river delta is subject to regular inundation from normal variation in precipitation.
Figure 2. Rock River floodwaters in downtown Fort Atkinson, Wisconsin.
286 Alexander Bolonkin
Floods from the sea can cause overflow or overtopping of flood-defenses like dikes as
well as flattening of dunes or bluffs. Land behind the coastal defence may be inundated or
experience damage. A flood from sea may be caused by a heavy storm (storm surge), a high
tide, a tsunami, or a combination thereof. As many urban communities are located near the
coast this is a major threat around the world.
Many rivers that flow over relatively flat land border on broad flood plains. When heavy
the deposition of silt on the rich farmlands and can result in their eventual depletion. The
annual cycle of flood and farming was of great significance to many early farming cultures,
most famously to the ancient Egyptians of the Nile river and to the Mesopotamians of the
Tigris and Euphrates rivers.
A flood happens when an area of land, usually low-lying, is covered with water. The
worst floods usually occur when a river overflows its banks. An example of this is the
January 1999 Queensland floods, which swamped south-eastern Queensland. Floods happen
when soil and vegetation cannot absorb all the water. The water then runs off the land in
quantities that cannot be carried in stream channels or kept in natural ponds or man-made
reservoirs.
Periodic floods occur naturally on many rivers, forming an area known as the flood plain.
These river floods usually result from heavy rain, sometimes combined with melting snow,
which causes the rivers to overflow their banks. A flood that rises and falls rapidly with little
or no advance warning is called a flash flood. Flash floods usually result from intense rainfall
over a relatively small area. Coastal areas are occasionally flooded by high tides caused by
severe winds on ocean surfaces, or by tidal waves caused by undersea earthquakes. There are
often many causes for a flood.
Monsoon rainfalls can cause disastrous flooding in some equatorial countries, such as
Bangladesh, Hurricanes have a number of different features which, together, can cause
devastating flooding. One is the storm surge (sea flooding as much as 8 metres high) caused
by the leading edge of the hurricane when it moves from sea to land. Another is the large
amounts of precipitation associated with hurricanes. The eye of a hurricane has extremely low
pressure, so sea level may rise a few metres in the eye of the storm. This type of coastal
flooding occurs regularly in Bangladesh.
In Europe floods from sea may occur as a result from heavy Atlantic storms, pushing the
water to the coast. Especially in combination with high tide this can be damaging.
Under some rare conditions associated with heat waves, flash floods from quickly
melting mountain snow have caused loss of property and life.
Undersea earthquakes, eruptions of island volcanos that form a caldera, (such as Thera or
Krakatau) and marine landslips on continental shelves may all engender a tidal wave called a
tsunami that causes destruction to coastal areas. See the tsunami article for full details of these
marine floods.
Floods are the most frequent type of disaster worldwide. Thus, it is often difficult or
impossible to obtain insurance policies which cover destruction of property due to flooding,
since floods are a relatively predictable risk.
• In 1983 the Pacific Northwest saw one of their worst winter floods. And the some of
the Northwest states saw their wettest winter yet. The damage was estimated at 1.1
billion dollars.* In 1965 Hurricane Betsy flooded large areas of New Orleans for up
to 10 days, drowning around 40 people.
New Concepts, Ideas and Innovations in Aerospace… 287
• In 1957, storm surge flooding from Hurricane Audrey killed about 400 people in
southwest Louisiana.
• The Hunter Valley floods of 1955 in New South Wales destroyed over 100 homes
and caused 45,000 to be evacuated.
• The North Sea Flood of 1953 caused over 2,000 deaths in the Dutch province of
Zeeland and the United Kingdom and led to the construction of the Delta Works and
the Thames Barrier.
• The Lynmouth flood of 1952 killed only 34 people, however it was very destructive
and destroyed over 80 buildings.
• The 1931 Huang He flood caused between 800,000 and 4,000,000 deaths in China,
one of a series of disastrous floods on the Huang He.
• The Great Mississippi Flood in 1927 was one of the most destructive floods in
United States history.
The 2005 tragedy of New Orleans shows that disregard of protection of the USA‘s
coastal cities (New York, Los Angles-San Pedro) from strong storm-caused waves, hurricane
storm surges, and small tsunamis gives rise to gigantic damages, material losses, human
deaths and injuries.
The Metropolitan East Coast (MEC) region -- with New York City at its center -- has
nearly 20 million people, a $1 trillion economy, and $2 trillion worth of built assets, nearly
half of which are complex infrastructure.
Many elements of transportation and other essential infrastructure systems in the MEC
region, and even some of its regular building stock, are located at elevations from 6 to 20 feet
above current sea level. This is well within the range of expected coastal storm surge
elevation of 8 to more than 20 feet for tropical (hurricanes) and extra-tropical storms.
Depending on which climate change scenarios apply, the sea level regional rise over the next
100 years will accelerate and amount to at most 3 feet by the year 2100. This seemingly
modest increase in sea level has the effect to raise the frequency of coastal storm surges and
related flooding by factors of 2 to 10, with an average of about 3.
The rate of financial losses incurred from these coastal floods will increase accordingly.
Expected annualized losses from coastal storms, already on the order of about $1 billion per
year, would be small enough to be absorbed by the $1 trillion economy of the region.
However, actual losses do not occur in regular annualized doses. Rather, they occur during
infrequent extreme events that can cause losses of hundreds of billions of dollars for the
largest events, albeit with low probability.
3. Brif information about cover film and liquid crystal. Our dome cover (film) has 5
layers (Figure 4): transparant dielectric layer, conducting layer (about 1 - 3 ), liquid crystal
layer (about 10 - 100 ), conducting layer (for example, SnO2), and transparant dielectric
layer. Common thickness is 0.1 - 0.5 mm. Control voltage is 5 - 10 V. Film is produced the
industry and it not expensive. Liquid crystals (LC) are substances that exhibit a phase of
matter that has properties between those of a conventional liquid, and those of a solid crystal.
Liquid crystals find wide use in liquid crystal displays (LCD), which rely on the optical
properties of certain liquid crystalline molecules in the presence or absence of an electric
field. The electric field can be used to make a pixel switch between clear or dark on
288 Alexander Bolonkin
command. Color LCD systems use the same technique, with color filters used to generate red,
green, and blue pixels.
Table 2. Ten deadliest natural disasters
Rank Event Location Date Death Toll
(Estimate)
1. 1931 Yellow River flood Yellow River, China Summer 1931 850,000-
4,000,000
2. 1887 Yellow River flood Yellow River, China September-October 1887 900,000-
2,000,000
3. 1970 Bhola cyclone Ganges Delta, East
Pakistan November 13, 1970 500,000-
1,000,000
4. Earthquake Eastern Mediterranean 1201 1,000,000
5. 1938 Yellow River flood Yellow River, China June 9th, 1938 500,000 -
900,000
6. Shaanxi Earthquake Shaanxi Province,
China January 23, 1556 830,000
7. 2004 Indian Ocean
earthquake/tsunami Indian Ocean December 26, 2004 225,000-
275,000
8. Tropical Cyclone Haiphong, Vietnam 1881 300,000
9. Flood Kaifeng, Henan
Province, China 1642 300,000
10. Earthquake Tangshan, China July 28, 1976 242,000*
* Official Government figure. Estimated death toll as high as 655,000.
Similar principles can be used to make other liquid crystal based optical devices. Liquid
crystal in fluid form is used to detect electrically generated hot spots for failure analysis in the
semiconductor industry. Liquid crystal memory units with extensive capacity were used in
Space Shuttle navigation equipment. It is also worth noting that many common fluids are in
fact liquid crystals. Soap, for instance, is a liquid crystal, and forms a variety of LC phases
depending on its concentration in water.
The conventional control clarity film reflected a superfluos energy back to space. If film
has solar cells that converts the superfluos solar energy into electricity.
2. DESCRIPTION AND INNOVATIONS
Our idea is a dome covering a big region (city, large bad area, country, continent) by a
thin film with control clarity (reflectivity, carrying capacity of solar spectrum). The film is
located at high altitude (4 - 6 km) which include the Earth's troposphere where are the main
climatic changes. The film is support at the altitude by a small additional air pressure
produced by ground ventilators and connected to Earth's ground by cables. The closed area is
also divided by sub-areas by film having control clarity. That allows to make different
conditions (solar heating) in sub-areas and pumping hot, warm, cold, moist air from one subarea
to other sub-area. There are a cheap film having liquid crystal and conducting layers. The
clarity of them is controlled by electric voltage. They can pass or blockade the solar light (or
New Concepts, Ideas and Innovations in Aerospace… 289
parts of solar spectrum) and pass or blockade the Earth radiation. The outer and incite
radiations have different wave lengths. That makes to control of them separately and to
control a heating of the Earth surface. In conventional conditions about 50% of the solar
energy reaches the Earth surface. The most part is reflected back to outer space by the white
clouds. In our closed system the clouts (and rain) will be made in a night when temperature is
low. That means the many cold regions (Alaska, Siberia) may be accepted more solar energy
and became a temperate climate or sub-tropic climate. That also means the Sahara desert can
be a prosperous area with fine climate and with closed-loop water cycle.
The building of film dome is very ease. We spread out the film over Earth surface, turn
on the pumping propellers and film is risen by air to needed altitude limited by the support
cables. The bid damage of film is not trouble because the additional air pressure is very small
and air leakage is compensated by propeller pumps.
The other advantages of the suggested method is possibility to pain the pictures on sky
(dome), to show films on the sky by projector, to suspend illuminations, decorations, and air
tramway. The long distance aircraft fly at altitude 8 - 11 km and our dome do not trouble for
it. The support cable will have illumination and internal helicopters also will avoid the contact
with them.
The people throw out hundreds the thin film plastic bags from purchases every month. If
we will collect them and use for the offered dome, we make fine our weather, get new
territory for living with wonderful climate.
Our design for the dome is presented in Figure 3, which includes the thin inflated film
dome. The innovations are listed here: (1) the construction is air-inflatable; (2) each dome is
fabricated with very thin, transparent film (thickness is 0.1 to 0.3 mm) having the control
clarity without rigid supports; (3) the enclosing film has two conductivity layers plus a liquid
crystal layer between them which changes its clarity, color and reflectivity under an electric
voltage (figure 4); (4) the bound section of dome has a hemisphere form (#5, Figure 3) . The
air pressure is more in these sections and they protect the central sections from outer wind.
Figure 3 illustrates the thin transparent control dome cover we envision. The inflated
textile shell—technical ―textiles‖ can be woven or non-woven (films)—embodies the
innovations listed: (1) the film is very thin, approximately 0.1 to 0.3 mm. A film this thin has
never before been used in a major building; (2) the film has two strong nets, with a mesh of
about 0.1 0.1 m and a = 1 1 m, the threads are about 0.5 mm for a small mesh and about 1
mm for a big mesh. The net prevents the watertight and airtight film covering from being
damaged by vibration; (3) the film incorporates a tiny electrically conductive wire net with a
mesh about 0.1 x 0.1 m and a line width of about 100 and a thickness near 10 . The wire
net is electric (voltage) control conductor.
Figure 3. Film dome over city. Notations: 1 - city, 2 - thin film cover with control clarity, 3 - support
cable, 4 - exits and ventilators, 5 - semi-cylindrical border section.
290 Alexander Bolonkin
Figure 4. Design of covering membrane. Notations: (a) Big fragment of cover with control clarity
(reflectivity, carrying capacity); (b) Small fragment of cover; (c) Cross-section of cover (film)having 5
layers; (d) Longitudinal cross-section of cover for cold regions; 1 - cover; 2 -mesh; 3 - small mesh; 4 -
thin electric net; 5 - cell of cover; 6 - tubes;: 7 - transparant dielectric layer, 8 - conducting layer (about
1 - 3 ), 9 - liquid crystal layer (about 10 - 100 ), 10 - conducting layer, and 11 - transparant dielectric
layer. Common thickness is 0.1 - 0.5 mm. Control voltage is 5 - 10 V.
It can inform the dome supervisors concerning the place and size of film damage (tears,
rips, etc.) ; (4) the film may be twin-layered with the gap — c = 1 m and b = 2 m—between
covering‘s layers for heat saving. In polar regions this multi-layered covering is the main
means for heat insulation and puncture of one of the layers wont cause a loss of shape
because the film‘s second layer is unaffected by holing; (5) the airspace in the dome‘s
covering can be partitioned, either hermetically or not; and (6) part of the covering can have a
very thin shiny aluminum coating that is about 1 for reflection of unnecessary solar radiation
in equatorial or polar regions [1].
3. THEORY AND COMPUTATIONS DOME
As wind flows over and around a fully exposed, nearly completely sealed inflated dome,
the weather affecting the external film on the windward side must endure positive air
pressures as the wind stagnates. Simultaneously, low air pressure eddies will be present on the
leeward side of the dome. In other words, air pressure gradients caused by air density
differences on different parts of the dome‘s envelope is characterized as the ―buoyancy
effect‖. The buoyancy effect will be greatest during the coldest weather when the dome is
heated and the temperature difference between its interior and exterior are greatest. In
New Concepts, Ideas and Innovations in Aerospace… 291
extremely cold climates such as the Arctic and Antarctic Regions the buoyancy effect tends to
dominate dome pressurization.
Our basic computed equations, below, are derived from a Russian-language textbook.
Solar radiation impinging the orbiting Earth is approximately 1400 W/m2
. The average Earth
reflection by clouds and the sub-aerial surfaces (water, ice and land) is about 0.3. The Earthatmosphere
adsorbs about 0.2 of the Sun‘s radiation. That means about q0 = 700 W/m2
s of
solar energy (heat) reaches our planet‘s surface at the Equator. Our troposphere dome does
not have clouds in light time and contains about 1/3 part of Earth atmosphere. That means we
can adsorb about 70 - 80% of solar energy. It is useful for polar regions and in winter time.
The solar spectrum is graphed in Figure 5.
Figure 5. Spectrum of solar irradiance outside atmosphere and at sea level with absorption of
electromagnetic waves by atmospheric gases. Visible light is 0.4 - 0.8 m , 400 – 800 nm.
The visible part of the Sun‘s spectrum is only = 0.4 to 0.8 .. Any warm body emits
radiation. The emission wavelength depends on the body‘s temperature. The wavelength of
the maximum intensity (see Figure 5) is governed by the black-body law originated by Max
Planck (1858-1947):
, [ ]
2.9
mm
T
m
(1)
where T is body temperature, oK. For example, if a body has an ideal temperature 20 oC (T =
293 oK), the wavelength is m = 9.9 .
292 Alexander Bolonkin
The energy emitted by a body may be computed by employment of the Josef StefanLudwig
Boltzmann law.
4 E ST , [W/m2
], (2)
where is coefficient of body blackness ( =0.03 0.99 for real bodies), s = 5.6710-8
[W/m2 .K] Stefan-Boltzmann constant. For example, the absolute black-body ( = 1) emits (at
T = 293 0K) the energy E = 418 W/m2
.
Amount of the maximum solar heat flow at 1 m2
per 1 second of Earth surface is
q = qo cos ( ) [W/m2
], (3)
where is Earth longevity, is angle between projection of Earth polar axis to the plate
which is perpendicular to the ecliptic plate and contains the line Sun-Earth and the
perpendicular to ecliptic plate. The sign "+" signifies Summer and the "-" signifies Winter, qo
700 W/m2
is the annual average solar heat flow to Earth at equator corrected for Earth
reflectance. For our case this magnitude can reach qo 1000 - 1100 W/m2
.
This angle is changed during a year and may be estimated for Earth's North Polar Region
hemisphere by the following the first approximation equation:
364
cos , where 2
N
m
(4)
where m is maximum , m = 23.5o =0.41 radian; N is number of day in a year. The
computations for Summer and Winter are presented in Figure 6.
Figure 6. Maximum Sun radiation flow at Earth surface via Earth latitude and season without dome.
New Concepts, Ideas and Innovations in Aerospace… 293
The heat flow for a hemisphere having reflector [1] at noon may be computed by
equation
cos sin q c1q0 S
(5)
where S is fraction (relative) area of reflector to service area of "Evergreen" dome [1]. For
reflector of Figure1 [1] S = 0.5; c1 is film transparency coefficient (c1 0.9 - 0.95).
The daily average solar irradiation (energy) is calculated by equation
Q 86400 c qt, where t 0.51 tan tan , tan tan 1
,
(6)
where c is daily average heat flow coefficient, c 0.5 without dome, c 0.75 with dome; t is
relative daily light time, 86400 = 246060 is number of seconds in a day.
The computation for relative daily light period is presented in Figure 7.
Figure 7. Relative daily light time via Earth latitude.
The heat loss flow per 1 m2
of dome film cover by convection and heat conduction is (see
[2]):
i
i i
q k t t k
1 2
1 2
1/ / 1/
1
, where
(7)
where k is heat transfer coefficient, W/m2.K; t1,2 are temperatures of the inter and outer multilayers
of the heat insulators, oC; 1,2 are convention coefficients of the inter and outer multi-
294 Alexander Bolonkin
layers of heat insulators ( = 30 100), W/m2K; i are thickness of insulator layers; i are
coefficients of heat transfer of insulator layers (see Table 1), m; t1,2 are temperatures of initial
and final layers o C.
The radiation heat flow per 1 m2
s of the service area computed by equations (2):
, 5.67
1/ 1/ 1
, where
100 100 1 2
4
2
4
1
s
s
r r c
c C
T T
q C
[W/m2K
4
], (8)
where Cr
is general radiation coefficient, are black body rate (emittance) of plates (see Table
2); T is temperatures of plates, oK.
The radiation flow across a set of the heat reflector plates is computed by equation
r
r
r q
C
C
q
0.5
(9)
where
Cr
is computed by equation (8) between plate and reflector.
The data of some construction materials is found in Table 3, 4.
Table 3. [11], p.331. Heat Transferring
Material Density,
kg/m3
Thermal conductivity,
W/m. oC
Heat capacity,
kJ/kg. oC
Concrete 2300 1.279 1.13
Baked brick 1800 0.758 0.879
Ice 920 2.25 2.26
Snow 560 0.465 2.09
Glass 2500 0.744 0.67
Steel 7900 45 0.461
Air 1.225 0.0244 1
As the reader will see, the air layer is the best heat insulator. We do not limit its thickness
.
Table 4. [11], p. 465. Emittance
Material Emittance, Material Emittance, Material Emittance,
Bright Al
Temperature
0.04 - 0.06
t = 50 500
o C
Baked brick
t = 20 o C
0.88 - 0.93 Glass
t = 20 100
o C
0.91 - 0.94
As the reader will notice, the shiny aluminum louver coating is excellent mean jalousie
against radiation losses from the dome.
New Concepts, Ideas and Innovations in Aerospace… 295
The general radiation heat Q computes by equation (6). Equations (1) – (9) allow
computation of the heat balance and comparison of incoming heat (gain) and outgoing heat
(loss).
The computations of heat balance of a dome of any size in the coldest wintertime of the
Polar Regions are presented in Figure 8.
Figure 8. Daily heat balance through 1 m2
of dome during coldest winter day versus Earth's latitude
(North hemisphere example). Data used for computations (see Eq. (1) - (9)): temperature inside of
dome is t1= +20o C, outside are t2 = -10, -30, -50o C; reflectivity coefficient of mirror is c2= 0.9;
coefficient transparency of film is c1 = 0.9; convectively coefficients are 1= 2 = 30; thickness of film
layers are 1= 2 =0.0001 m; thickness of air layer is = 1 m; coefficient of film heat transfer is 1= 3
= 0.75, for air 2 = 0.0244; ratio of cover blackness 1= 3 = 0.9, for louvers 2 = 0.05.
The thickness of the dome envelope, its sheltering shell of film, is computed by formulas
(from equation for tensile strength):
Rp Rp
1
,
2
2
(10)
where 1 is the film thickness for a spherical dome, m; 2 is the film thickness for a
cylindrical dome, m; R is radius of dome, m; p is additional pressure into the dome, N/m2
;
is safety tensile stress of film, N/m2
.
The dynamic pressure from wind is
2
2 V
pw
(11)
296 Alexander Bolonkin
where = 1.225 kg/m3
is air density; V is wind speed, m/s.
For example, a storm wind with speed V = 20 m/s, standard air density is = 1.225
kg/m3
. Then dynamic pressure is pw = 245 N/m2
. That is four time less when internal pressure
p = 1000 N/m2
. When the need arises, sometimes the internal pressure can be voluntarily
decreased, bled off.
In Figure 8 the alert reader has noticed: the daily heat loss is about the solar heat in the
very coldest Winter day when a dome located above 600 North or South Latitude and the
outside air temperature is –50 0C.
In [1] we show the heat loss of the dome in Polar region is less than 14 times the heat of
the buildings inside unprotected by an inflated dome.
We consider a two-layer dome film and one heat screen. If needed, better protection can
further reduce the head losses as we can utilize inflated dome covers with more layers and
more heat screens. One heat screen decreases heat losses by 2, two screens can decrease heat
flow by 3 times, three by 4 times, and so on. If the Polar Region domes have a mesh structure,
the heat transfer decreases proportional to the summary thickness of its enveloping film
layers.
The dome shelter innovations outlined here can be practically applied to many climatic
regimes (from Polar to Tropical). The North and South Poles may, during the 21st Century,
become places of cargo and passenger congregation since the a Cable Space Transportation
System, installed on Antarctica‘s ice-cap and on a floating artificial ice island has been
proposed the would transfer people and things to and from the Moon.1
4. DISCUSSION
As with any innovative macro-project proposal, the reader will naturally have many
questions. We offer brief answers to the four most obvious questions our readers are likely to
ponder.
(1) How can snow and ice be removed from the dome? The rain, snow clouds located in
Earth troposphere lower 4 km altitude. Our dome has height 4 - 6 km. If water
appears over film, it flows down through special opening. If snow appears over film,
the control made the black film, the sun flux the snow. The film cover is flexible and
has a lift force of about 1 -100 kg/m2
. We imagine that a controlled change of interior
air pressure will serve to shake the snow and ice off.
(2) Storm wind. The storm wind can be only on bounding sections of dome. They are
special semi-cylindrical form (Figure3) and more strong then central sections.
(3) Cover damage. The envelope contains a cable mesh so that the film cannot be
damaged greatly. Electronic signals alert supervising personnel of any rupture
problems.
(4) What is the design life of the film covering? Depending on the kind of materials used,
it may be as much a decade. In all or in part, the cover can be replaced periodically.
New Concepts, Ideas and Innovations in Aerospace… 297
5. CONCLUSION
The control of Regional and Global Earth Weather is important problem of humanity.
That dramatically increases the territory suitable for men living, sown area, crop capacity.
That allows to convert all Earth lend such as Alaska, North Canada, Siberia, deserts Sahara or
Gobi in prosperous garden. The suggested method is very cheap (cost of covering 1 m2
is
about 2 - 15 cents) and may be utilized at present time. We can start from small area, from
small towns in bad regions and extended in large area.
Film domes can foster the fuller economic development of cold regions such as the
Earth‘s Arctic and Antarctic and, thus, increase the effective area of territory dominated by
humans. Normal human health can be maintained by ingestion of locally grown fresh
vegetables and healthful ―outdoor‖ exercise. The domes can also be used in the Tropics and
Temperate Zone. Eventually, they may find application on the Moon or Mars since a vertical
variant, inflatable towers to outer space, are soon to become available for launching
spacecraft inexpensively into Earth-orbit or interplanetary flights. The closed problems are
researched in references [1]-[10].
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: "Bolonkin", and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Bolonkin, A.A. and R.B. Cathcart, Inflatable ‗Evergreen‘ Dome Settlements for Earth‘s
Polar Regions. Clean. Techn. Environ. Policy. DOI 10.1007/s10098.006-0073.4.
[2] Bolonkin, A.A. and R.B. Cathcart, ―A Cable Space Transportation System at the
Earth‘s Poles to Support Exploitation of the Moon‖, Journal of the British
Interplanetary Society 59: 375-380, 2006.
[3] Bolonkin A.A., Cheap Textile Dam Protection of Seaport Cities against Hurricane
Storm Surge Waves, Tsunamis, and Other Weather-Related Floods, 2006.
http://arxiv.org.
[4] Bolonkin, A.A. and R.B. Cathcart, Antarctica: A Southern Hemisphere Windpower
Station? 2006. http://Arxiv.org.
[5] Cathcart R.B. and Bolonkin, A.A. Ocean Terracing, 2006. http://arxiv.org. 6. Bolonkin,
A.A. and R.B. Cathcart, The Java-Sumatra Aerial Mega-Tramway, 2006.
http://arxiv.org.
[6] Bolonkin, A.A., ―Optimal Inflatable Space Towers with 3-100 km Height‖, Journal of
the British Interplanetary Society Vol. 56, pp. 87 - 97, 2003.
[7] Bolonkin A.A., Non-Rocket Space Launch and Flight, Elsevier, London, 2006, 488 ps.
[8] Bolonkin A.A., Cathcart R.B., Inflatable ‗Evergreen‘ Polar Zone Dome (EPZD)
Settlements, 2006. http://arxiv.org.
[9] Macro-Engineering: A Challenge for the Future. Springer, 2006. 318 ps. Collection of
articles.
[10] Naschekin, V.V., Technical thermodynamic and heat transmission. Public House High
University, Moscow. 1969 (in Russian).
New Concepts, Ideas and Innovations in Aerospace…
Chapter 4
CONVERTING OF DESERTS AND POLAR EARTH
REGIONS IN GARDENS
ABSTRACT
Sustaining human life at the Earth‘s antipodal Polar Regions is very difficult
especially during Winter when water-freezing air temperature, blizzards and "whiteouts"
make normal human existence dangerous. To counter these environmental stresses, we
offer the innovative artificial "Evergreen" Polar Zone Dome (EPZD), an inflated halfhemisphere
with interiors continuously providing a Mediterranean Sea-like climate. The
"Evergreen" EPZD structural theory is developed, substantiated by key computations that
show it is possible for current building technology to construct and heat large enclosed
volumes inexpensively. Specifically, a satisfactory result is reached by using sunlight
reflectors and a special double thin film, which concentrates all available solar energy
inside the EPZD while, at the same time markedly decreasing the heat loss to exterior
Polar Region air. Someday a similar, but remarkably more technological, EPZD design
may be employed at proposed Moon and Mars settlements.
Keywords: artificial hemisphere, inflatable film building, Polar Region homes, solar
energy concentrator.
I.INTRODUCTION
Particularly during Winter, the Earth‘s two Polar Regions provide only a meager and
uncomfortable life-style for humans, featuring very low ambient air temperature, strong wind,
and seasonal darkness. Starting from Cape Artichesky (Russia), Mike Horn and Borge
Ousland completed, during January to March 2006, the first known over-pack ice trek to the
planet‘s geographic North Pole during darkness! More persons are likely to undertake such
journeys near the Arctic Ocean‘s coast when permanent dwellings are situated closer to the
North Pole. The purpose of our report is to make possible economical new cities at both Polar
Regions of the Earth.
Economists allege that the mean 2006 USA Dollar value of Polar Region land territory is
generally low compared to the world total of ~$250,000/km2
. For example: Antarctica
Kept in http://arxiv.org as paper by A. Bolonkin and R. Cathcart.
300 Alexander Bolonkin
~$40/km2
, Greenland ~$650/km2
, Canada ~$77,000/km2
and Russia ~$106,000/km2
.
However, world economic productivity data show that the 2006 USA dollar output per capita
in the Earth-biosphere is greatest in Polar Regions; cold regions have output per capita that is
approximately 10-12 times that of the Earth‘s Tropic Zones! The distance north or south from
the planet‘s Equator is amongst the most significant measured environmental variables
underlying the differences expressed in per capita USA dollar output by country-ecosystem,
but this is probably explained by the overall global pattern of human settlement, which tends
to influence social institutions and their supportive technologies [1].
In other words, if persons living at the Polar Regions were made more comfortable than
now, it is very probable that the economic value per square kilometer of territory situated in
those two geographical regions would decrease slightly since only very poor persons
(nomadic natives in the Northern Hemisphere) and highly paid persons (technicians and
scientists [2]) dwell fulltime in the Earth‘s Polar Regions nowadays! Non-nomadic people
currently work in these uncomfortably cold and seasonally dark climate settlements only
because there are known mineral, natural gas and petroleum deposits to be mined, along with
seasonal and non-seasonal hydroelectric facilities [3] to be efficiently operated for the benefit
of large populations living in warmer climates away from primary production places. There is
every reason to think that valuable Arctic and Antarctica resources remain undiscovered,
awaiting future exploration and industrial exploitation. The Arctic alone has proven
discovered oil and natural gas deposits equal to 40% of Saudi Arabia‘s total reserves [4].
Many people worldwide, especially in the Temperate Zones, muse on the possibility of
humans someday inhabiting orbiting Space Settlements and Moon Bases or a terraformed
Mars but few seem to contemplate an increased use of ~25% of Earth‘s surface—the Polar
Regions [5]. Antarctica is being investigated for its economic potential [6] and already the
Antarctic Circumpolar Current has been affected by global civilization [7].
II. ARCTIC
Geoscience has generally substantiated that the Arctic is warming and eventually it may
reach a seasonally ―ice-free‖ state caused by the absence of new sea-ice due to non-formation
as well as summertime excess sublimation of glaciers on land during the 21st Century [8].
Climatological feedback loops, which effect change, are the interplay between sea/land ice,
North Atlantic Ocean currents—especially the Gulf Stream and the north-flowing current in
the Bering Strait—and the annual amounts of precipitation and evaporation in the Arctic.
Reduced sea-ice extent and thickness in the Arctic Ocean would promote regular summertime
commercial shipping, and present new opportunities for offshore oil and gas extraction. A
Northern Sea Route paralleling the Siberian coastline would be ~40% shorter than the current
Europe-Asia Route which requires a passage through the Suez Canal [9]. In addition, new
macroprojects—opportunistic hydroelectric power development of diminishing glaciers and a
permanent tunnel or bridge15 across the Bering Strait—may attract new settlers to the Arctic.
There is also the possibility, as we explore here, for Arctic Zone greenhouses under inflated
membrane half-hemispheres producing fresh fruits and vegetables for workers on such
macroprojects and to luxuriously house at low-cost workers seeking to maintain the presentday
natural stock of Arctic Ocean sea-ice by construction of artificial ice islands [10].
New Concepts, Ideas and Innovations in Aerospace… 301
III. ‘EVERGREEN’ INFLATED DOMES
Possibly the first true architectural attempt at constructing effective artificial life-support
systems in climatically harsh regions in the Earth-biosphere was the building of greenhouses.
Extensive commercial greenhouses in The Netherlands—and even outer space [11]—are
maintained nearly automatically by heating, cooling, irrigation, nutrition and plant disease
management equipment. The ―Climatron‖ greenhouse was finished in 1959 at the Missouri
Botanical Garden in St. Louis, USA, while the world‘s most voluminous greenhouses, the
Eden Project, were completed in Cornwall, UK during the early 21st Century [12]. All people
share commonalities in their responses to natural environmental stresses that are stimulated
by extremely cold air, snowstorms and strong wind. In the Arctic and Antarctica, lifethreatening
―whiteout‖ snowstorms inflict somewhat the same personal visual discomfort and
disorientation as cosmonauts/astronauts experience during their space-walks—that of being
adrift in featureless outer space! With special clothing and shelters, humans can adapt to these
Polar Regions successfully. Medical researchers have asserted that ―…cold-related deaths are
far more numerous than heat-related deaths in the United States, Europe, and almost all
countries outside of the tropics, and almost all of them are due to common illnesses that are
increased by cold‖ [13]. Incontrovertibly, living near the planet‘s poles is stressful and
operationally difficult, even when tempered by strong conventional buildings such as those at
the Earth‘s South Pole where the Ozone Hole causes a UVB radiation hazard that cannot be
ignored because it helps cause sunburn (erythema) and snow blindness (photokeratitis); the
Arctic also has a UVB radiation hazard. The morale of personnel—a difficult factor to
measure—during wintertime when little daylight and little contrast between land, sea and sky
predominates can cause monotony, a negative influence on personnel activity and efficiency.
Essentially, any EPZD becomes the total environment of its inhabitants, so proper internal
temperature control and soundproofing are vital. Relative humidity inside the EPZD ought to
be fixed at 30-40% for human comfort and health reasons and to insure that static electricity
does not become a problem affecting safety in the EPZD.
The first ―Evergreen‖-type dwelling hemisphere design ―City in the Arctic‖ was
commissioned by Germany‘s Farbwerke Hoechst AG in 1970 [14]. ―City in the Arctic‖ was a
pneumatically stabilized climate-regulating transparent membrane half-sphere shell with a
diameter 2,000 to 2,200 m and a height of about 240 m intended to comfortably enable
15,000 to 45,000 workers. The contemplated membrane was to be reinforced and supported
by a net of intersecting, braided polyester fiber cables. Better 21st Century materials are
available that would improve the formidable performance characteristics of ―City in the
Arctic‖ [15]. Founded in 1956, Birdair, Inc. in the USA, introduced its SheerfillTM in 1970
and this constantly improved material offers translucencies of ~25%. The energy impact of
Sheerfill, and other nearly non-combustible architectural technical textiles [16], is a function
of the tradeoff between decreased lighting needs and increased heating costs; a dynamic airsupported
membrane building normally costs only about 33% of a building assembled with
ordinary materials [17]. (More technologies will be revealed at The Twelfth International
Workshop on the Design and Practical Realization of Architectural Membrane Structures,
―Textile Roofs 2007‖, held 7-9 June 2007 in Berlin, Germany.) ―City in the Arctic‖ was never
302 Alexander Bolonkin
built because it was merely an architectural speculation, even less substantial than the
architectural speculations of Sotirios Kotoulas in Space Out (Springer, 2006).
Our macro-engineering concept of inexpensive-to-construct and operate ―Evergreen‖
inflated Earth-surface domes is supported by computations, making our macroproject
speculation more than a daydream. However, we lack access to a low-speed laboratory wind
tunnel and that inhibits our apprehension of wall interference and the effect of some layout
details, such as open or closed doors facing the EPZD exterior. Innovations are needed, and
wanted, to realize such structures in the Polar Regions of our unique but continuously
changing planet.
IV. DESCRIPTION AND INNOVATIONS
Our design for an Arctic people-housing ―Evergreen‖ dome is presented in Figure 1,
which includes the thin inflated film dome. Air-supported construction derives from the
balloon principle to shape a building; the air pressure inside the building exceeds the external
air pressure to support the roof. Sunlight can penetrate special roofing materials, making the
interiors brighter than others types of constructed buildings. The EPZD innovations are listed
here: (1) the construction is air-inflatable; (2) each dome is fabricated with very thin,
transparent film (thickness is 0.1 to 0.2 mm) without rigid supports; (3) the enclosing film is a
two-layered element with air between the layers to provide insulation; (4) the construction
form is that of a hemisphere, or in the instance of a roadway/railway a half-tube, and part of it
has a thin aluminum layer about 1 or less that functions as the gigantic collector of solar
incident solar radiation (heat). Surplus heat collected may be used to generate electricity or
furnish mechanical energy; and (5) the dome is equipped with sunlight controlling louvers
[AKA, ―jalousie‖, a blind or shutter having adjustable slats to regulate the passage of air and
sunlight] with one side thinly coated with reflective polished aluminum of about 1 . Realtime
control of the sunlight‘s entrance into the dome and nighttime heat‘s exit is governed by
the shingle-like louvers.
Figure 1 illustrates the thin transparent dome cover we envision. The hemispherical
inflated textile shell—technical ―textiles‖ can be woven or non-woven (films)—embodies the
EPZD innovations listed: (1) the film is very thin, approximately 0.1 to 0.2 mm. A film this
thin has never before been used in a major building; (2) the film has two strong nets, with a
mesh of about 0.1 0.1 m and a = 1 1 m, the threads are about 0.3 mm for a small mesh
and about 1 mm for a big mesh. The net prevents the watertight and airtight film covering
from being damaged by vibration; (3) the film incorporates a tiny electrically conductive wire
net with a mesh about 0.01 x 0.01 m and a line width of about 100 and a thickness near 1.
The wire net can inform the ―Evergreen‖ dome supervisors concerning the place and size of
film damage (tears, rips, etc.); (4) the film is twin-layered with the gap — c = 1 m and b = 2
m—between covering‘s layers. This multi-layered covering is the main means for heat
insulation and puncture of one of the layers wont cause a loss of shape because the film‘s
second layer is unaffected by holing; (5) the airspace in the dome‘s covering can be
partitioned, either hermetically or not; (6) the units #5 of the cover is furnished with a heat
tube #6 that can spray warmed anti-freeze liquid onto the EPZD‘s exterior, thus eliminating
New Concepts, Ideas and Innovations in Aerospace… 303
snow and ice buildup; and (7) part of the covering has a very thin shiny aluminum coating
that is about 1 for reflection of incoming solar radiation.
Figure 1. Artificial inflatable dome for Earth‘s Northern Hemisphere cold regions. Notations: (a) crosssection
area of suggested biosphere; (b) top view of cylindrical biosphere, 1 - transparence thin double
film ("textiles"); 2 - reflected cover of half-hemisphere; 3 - control louvers (jalousie); 4 - solar beams
(light); 5 - enter; 6 - air pump (ventilator).
Figure 2. Design of membrane cover. Notations: (a) Big fragment of cover; (b) Small fragment of
cover; (c) Cross-section of cover; (d) Longitudinal cross-section of cover; 1 - cover; 2 -mesh; 3 - small
mesh; 4 - thin electric net; 5 - sell of cover; 6 - tubes; 7 - film partition (non hermetic); 8 - perpendicular
cross-section area.
304 Alexander Bolonkin
Figure 3 illustrates a lightweight, possibly portable house using the same essential
construction materials as the dwelling/workplace shown in Figure 1.
Figure 3. Inflatable film house for cold climate regions. Notation: (a) Cross-section area; (b) Top view.
The other notations are same with Figure1.
Figure 5. Current inflatable dome.
V. THEORY AND COMPUTATIONS EPZD
The theory of polar settlement are same the theory in Chapter 4A (see equation (1) - (11),
figures 5 - 8, and tables 3, 4 in previous section. The additional estimations are below.
New Concepts, Ideas and Innovations in Aerospace… 305
The heating by combusted fuel is found by equation
Q = ct m/ , (1)
where ct
is heat rate of fuel [J/kg]; ct = 40 MJ/kg for liquid oil fuel; m is fuel mass, kg; is
efficiency of heater, = 0.5 - 0.8.
The thickness of the dome envelope, its sheltering shell of film, is computed by formulas
(from equation for tensile strength):
Rp Rp
1
,
2
2
(2)
where 1 is the film thickness for a spherical dome, m; 2 is the film thickness for a
cylindrical dome, m; R is radius of dome, m; p is additional pressure into the dome, N/m2
;
is safety tensile stress of film, N/m2
.
For example, compute the film thickness for dome having radius R =100 m, additional air
pressure p = 0.01 atm (p = 1000 N/m2
), safety tensile stress = 50 kg/mm2
( = 5108 N/m2
),
cylindrical dome.
0.0002m 0.2 mm
5 10
100 1000
8
(3)
The dynamic pressure from wind is
2
2 V
pw
(4)
where = 1.225 kg/m3
is air density; V is wind speed, m/s.
For example, a storm wind with speed V = 20 m/s, standard air density is = 1.225
kg/m3
. Then dynamic pressure is pw = 245 N/m2
. That is four time less than internal pressure
p = 1000 N/m2
. When the need arises, sometimes the internal pressure can be voluntarily
decreased, bled off.
In Figure 8 Ch.4A the alert reader has noticed: the daily heat loss is about the solar heat
in the very coldest Winter day when a dome located above 600 North or South Latitude and
the outside air temperature is –50 0C.
Let us compute and compare the heat extension for conventional buildings located on
same region with and without the ―Evergreen‖ dome.
Assume the two-story building, perhaps a home or small office, occupies 0.1 part of
domed area. That means their walls and roof is equal to 0.5 part of dome area. Assume the
building walls have a thickness of 0.2 m and are formed of baked bricks ( = 0.758 W/m.K).
The differences of temperature are 20 + 50 = 70 0C (T1 = 293 0K, T2 = 223 0K). So, 1 m2
of
building surface has a heat loss, in 1 second
q = 0.7580.570/0.2 = 132.65 W/m2
.s .
306 Alexander Bolonkin
The radiation heat loss from 1 m2
dome at night when the jalousies are closed tightly is
[Eq. (8-9), Ch. 4A]:
q C T T W m s
C
C
r
S
r
4 2
2
4
1
1 2
0.5 [(0.01 ) (0.01 ) ] 6.86 /
0.28 ,
1/ 0.05 1/ 0.9 1
5.67
1/ 1/ 1
(5)
Transfer and convective heat losses is (for 1 = 3 = 0.0001 m, 2 = 1 m, 1 =3 = 0.744,
2 = 0.0244, = 30) (see Eq. (7), Ch. 4A):
2
1 2 0.5 ( ) 1.57 0.025 70 2.75 /
0.025 ,
2 / 30 0.0002/ 0.744 1/ 0.0244
1
q k t t W m
k
(6)
Transfer heat loss is 6.86 + 2.75 = 9.61 W/m2
< 132.62 W/m2
. The heat loss of the dome
is less than 14 times the heat of the buildings inside unprotected by an inflated dome.
We consider a two-layer dome film and one heat screen. If needed, better protection can
further reduce the head losses as we can utilize inflated dome covers with more layers and
more heat screens. One heat screen decreases heat losses by 2, two screens can decrease heat
flow by 3 times, three by 4 times, and so on. If the Polar Region domes have a mesh structure,
the heat transfer decreases proportional to the summary thickness of its enveloping film
layers.
VI. MACROPROJECTS
The EPZD innovations outlined here can be practically applied to other climatic regimes
(from Polar to Tropical). We suggest initial macroprojects could be small (10 m diameter)
houses (Figure 3) followed by an ―Evergreen‖ dome in the Arctic or Antarctica covering a
land area 200 1000 m, with irrigated vegetation, homes, open-air swimming pools,
playground.
The house and ―Evergreen‖ dome have several innovations: Sun reflector, double
transparent insulating film, controllable jalousies coated with reflective aluminum and an
electronic cable mesh inherent to the film for dome safety/integrity monitoring purposes. By
undertaking to construct a half-sphere house, we can acquire experience in such constructions
and explore more complex constructions. By computation, a 10 m diameter home has a useful
floor area of 78.5 m2
, airy interior volume of 262 m3
covered by an envelope with an exterior
area of 157 m2
. It film enclosure material would have a thickness of 0.0002 mm with a total
mass of 65 kg.
A city-enclosing ―Evergreen‖ dome of 200 1000 m (Figure 1, with spherical end caps)
could have calculated characteristics: useful area = 2.3 105
m
2
, useful volume 17.8 106
m
3
, exterior dome area of 3.75 105
m
2
comprised of a film of 0.0002 mm thickness and 145
New Concepts, Ideas and Innovations in Aerospace… 307
tonnes. If the ―Evergreen‖ dome were formed with concrete 0.2 m thick, the mass of the citysize
envelope would be 173 103
tonnes, which is a thousand times heavier. Also, just for
comparison, if we made a gigantic ―Evergreen‖ dome with stiff glass, thousands of tonnes of
steel, glass would be necessary and such materials would be very costly to transport hundreds,
possibly thousands, of kilometers to the site where they would be assembled by highly-paid
workers. Our non-woven textile (film) is flexible and plastic can be relatively cheap. The
single greatest boon to ―Evergreen‖ dome construction, whether in the Earth‘s Polar Regions
or elsewhere, is the protected cultivation of plants within a dome that generates energy from
the available and technically harnessed sunlight. However, the North and South Poles may,
during the 21st Century, become places of cargo and passenger congregation since a Cable
Space Transportation System, installed on Antarctica‘s ice-cap and on a floating artificial ice
island has been proposed the would transfer people and things to and from the Moon [18].
Figure 6. Current inflatable dome.
VII. DISCUSSION
As with any innovative macroproject proposal, the reader will naturally have many
questions. We offer brief answers to the four most obvious questions our readers are likely to
ponder.
(1) How can snow and ice be removed from the dome? After a snowfall, weather
conditions permitting, a helicopter can hover over the dome, blowing off the
accumulated loose snow. Compacted snow and ice can be removed by activating
308 Alexander Bolonkin
remotely operated sprayers that squirt warmed anti-freeze liquid onto the dome‘s
exterior. Such deicer must not be toxic like those currently used at airports [19]. The
film cover is flexible and has a lift force of about 100 kg/m2
. We imagine that a
controlled change of interior air pressure will serve to shake the snow and ice off.
Such a technology is used in aircraft for wing de-icing.
(2) Storm wind. This was thoroughly considered in Section V, above.
(3) Cover damage. The envelope contains a cable mesh so that the film cannot be
damaged greatly. Its double layering structure governs the escape of heated air inside
the living zone. Electronic signals alert supervising personnel of any rupture
problems and permit a speedy repair effort by well-trained persons.
(4) What is the design life of the film covering? Depending on the kind of materials used,
it may be as much a decade. In all or in part, the cover can be replaced periodically.
VIII. CONCLUSION
―Evergreen‖ domes can foster the fuller economic development of cold regions such as
the Earth‘s Arctic and Antarctic and, thus, increase the effective area of territory dominated
by humans. Normal human health can be maintained by ingestion of locally grown fresh
vegetables and healthful ―outdoor‖ exercise. ―Evergreen‖ domes can also be used in the
Tropics and Temperate Zone. Eventually, they may find application on the Moon or Mars
since a vertical variant, inflatable towers to outer space [20], are soon to become available for
launching spacecraft inexpensively into Earth-orbit or interplanetary flights [22-25].
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: "Bolonkin", and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Hall, R.E. and Jones, C.I. (1999) ―Why Do Some Countries Produce So Much More
Output Per Worker Than Others?‖, Quarterly Journal Economics 114: 83-116.
[2] Klein, S. and Halzen, F. (May 2005) ―The ice cube at the end of the world‖, CERN
Courier, pages 17-22.
[3] Hornig, J.F. (Ed.) Social and Environmental Impacts of the James Bay Hydroelectric
Project, McGill-Queens University Press, Canada, 1999.
[4] Talley, I. (11 July 2006), ―Arctic Harshness Hinders Search for Oil‖, The Wall Street
Journal CCXLVIII: A10.
[5] Bolonkin, A.A. and R.B. Cathcart (2006), ―Inflatable ‗Evergreen‘ dome settlements for
Earth‘s Polar Regions‖, Clean Technologies and Environmental Policy DOI
10.1007/s10098-006-0073-4.
[6] Floren, D.W., (2001), ―Antarctic Mining Regimes: An Appreciation of the Attainable‖,
Journal of Environmental Law and Litigation 16: 467.
[7] Fyfe, J.C. and Saenko, O.A. (2005), ―Human-Induced Change in the Antarctic
Circumpolar Current‖, Journal of Climate 18: 3068-3073.
New Concepts, Ideas and Innovations in Aerospace… 309
[8] Overpeck, J.T. et al. (2005), ―Arctic System on Trajectory to New, Seasonally Ice-Free
State‖, EOS, Transactions of the American Geophysical Union 34: 309, 312-313.
[9] Walsh, Don (2007), ―Losing its Cool‖, Proceedings of the U.S. Naval Institute 133: 88.
[10] Zhou, S. and Flynn, P.C. (2005), ―Geoengineering Downwelling Ocean Currents: A
Cost Assessment‖, Climatic Change 71: 203-220.
[11] Albright, L.D., (2001) ―Environmental Control for Plants on Earth and in Space‖, IEEE
Control Systems Magazine 21: 28-47.
[12] GOTO: http://www.edenproject.org.uk/
[13] Keating, W.R. and Donaldson, G.C. (2004), ―The impact of global warming on health
and mortality‖, Southern Medical Journal 97: 1093-1099.
[14] Hix, J., The Glass House. MIT Press, Cambridge, USA, 1974, pages 192-196.
[15] Braddock-Clarke, S.E. and M. O‘Mahony, Techno Textiles 2. Thames & Hudson, NY,
USA, 2006.
[16] McQuaid, M. (Ed.), Extreme Textiles: Designing for High Performance. Princeton
Architectural Press, NY, USA, 2005.
[17] Koch, K-M. (Ed.), Membrane Structures: Innovative Building with Film and Fabric.
Prestel, NY, USA. 2004.
[18] Bolonkin, A.A. and R.B. Cathcart, (2006) ―A Cable Space Transportation System at the
Earth‘s Poles to Support Exploitation of the Moon‖, Journal of the British
Interplanetary Society 59: 375-380.
[19] `Corsi, S.R. et al., (2006), ―Characterization of Aircraft Deicer and Anti-Icer
Components and Toxicity in Airport Snowbanks and Snowmelt Runoff‖, Environ. Sci.
Technol. 40: 3195-3202.
[20] Bolonkin, A.A., (2003), ―Optimal Inflatable Space Towers with 3-100 km Height‖,
Journal of the British Interplanetary Society Vol. 56, pp. 87 - 97.
[21] Bolonkin A.A., (2006), "Non-Rocket Space Launch and Flight", Elsevier, London, 488
pgs.
[22] Bolonkin A.A., (2006), Cheap Textile Dam Protection of Seaport Cities against
Hurricane Storm Surge Waves, Tsunamis, and Other Weather-Related Floods. Printed
in http://arxiv.org.
[23] Bolonkin A.A., (2006), Control of Regional and Global Weather. Printed in
http://arxiv.org
[24] Bolonkin, A.A. and R.B. Cathcart (2006), Antarctica: A Southern Hemisphere
Windpower Station? Printed in http://arxiv.org
[25] Bolonkin, A.A. and R.B. Cathcart (2006), A Low-Cost Natural Gas/Freshwater Aerial
Pipeline. Printed in http://arxiv.org.
New Concepts, Ideas and Innovations in Aerospace…
Chapter 5
CHEAP TEXTILE DAM PROTECTION OF SEAPORT
CITIES AGAINST HURRICANE STORM SURGE
WAVES, TSUNAMIS, AND OTHER WEATHERRELATED
FLOODS
ABSTRACT
Author offers to complete research on a new method and cheap applicatory design
for land and sea textile dams. The offered method for the protection of the USA‘s major
seaport cities against hurricane storm surge waves, tsunamis, and other weather-related
inundations is the cheapest (to build and maintain of all extant anti-flood barriers) and it,
therefore, has excellent prospective applications for defending coastal cities from natural
weather-caused disasters. It may also be a very cheap method for producing a big amount
of cyclical renewable hydropower, land reclamation from the ocean, lakes, riverbanks, as
well as land transportation connection of islands, and islands to mainland, instead of very
costly over-water bridges and underwater tunnels.
Keywords: textile dam, protection of cities against hurricane threats, protection against
tsunami, flood protection, hydropower stations, land reclamation.
INTRODUCTION
In this statement, we consider the protection of important coastal urbanized regions
against tropical cyclone (hurricane), tsunami, and other such costly inundations. The
hurricane, storm and other weather disaster were described in Chapter 3A. Now we shortly
describe tsunami.
A tsunami is a series of waves when a body of water, such as an ocean is rapidly
displaced on a massive scale. Earthquakes, mass movements above or below water, volcanic
eruptions and other underwater explosions, landslides and large meteorite impacts all have the
Kept in http://arxiv.org
312 Alexander Bolonkin
potential to generate a tsunami. The effects of a tsunami can range from unnoticeable to
devastating. Tsunamis are common throughout Japanese history, as 195 events in Japan have
been recorded.
Tsunami
A tsunami has a much smaller amplitude (wave heights) offshore, and a very long
wavelength (often hundreds of kilometres long), which is why they generally pass unnoticed
at sea, forming only a passing "hump" in the ocean.
Tsunamis can be generated when the sea floor abruptly deforms and vertically displaces
the overlying water. Such large vertical movements of the Earth‘s crust can occur at plate
boundaries. Subduction earthquakes are particularly effective in generating tsunamis. As an
Oceanic Plate is subducted beneath a Continental Plate, it sometimes brings down the lip of
the Continental with it. Eventually, too much stress is put on the lip and it snaps back,
sending shockwaves through the Earth‘s crust, causing a tremor under the sea, known as an
Undersea Earthquake.
Sub-marine landslides (which are sometimes triggered by large earthquakes) as well as
collapses of volcanic edifices may also disturb the overlying water column as sediment and
New Concepts, Ideas and Innovations in Aerospace… 313
rocks slide downslope and are redistributed across the sea floor. Similarly, a violent
submarine volcanic eruption can uplift the water column and form a tsunami.
Tsunamis are surface gravity waves that are formed as the displaced water mass moves
under the influence of gravity and radiate across the ocean like ripples on a pond.
In the 1950s it was discovered that larger tsunamis than previously believed possible
could be caused by landslides, explosive volcanic action and impact events. These
phenomena rapidly displace large volumes of water, as energy from falling debris or
expansion is transferred to the water into which the debris falls. Tsunamis caused by these
mechanisms, unlike the ocean-wide tsunamis caused by some earthquakes, generally dissipate
quickly and rarely affect coastlines distant from the source due to the small area of sea
affected. These events can give rise to much larger local shock waves (solitons), such as the
landslide at the head of Lituya Bay which produced a water wave estimated at 50 – 150 m and
reached 524 m up local mountains. However, an extremely large landslide could generate a
megatsunami that might have ocean-wide impacts.
While it is not possible to prevent a tsunami, in some particularly tsunami-prone
countries some measures have been taken to reduce the damage caused on shore. Japan has
implemented an extensive programme of building tsunami walls of up to 4.5 m (13.5 ft) high
in front of populated coastal areas. Other localities have built floodgates and channels to
redirect the water from incoming tsunamis. However, their effectiveness has been questioned,
as tsunamis are often higher than the barriers. For instance, the tsunami which hit the island of
Hokkaido on July 12, 1993 created waves as much as 30 m (100 ft) tall - as high as a 10-story
building. The port town of Aonae was completely surrounded by a tsunami wall, but the
waves washed right over the wall and destroyed all the wood-framed structures in the area.
The wall may have succeeded in slowing down and moderating the height of the tsunami but
it did not prevent major destruction and loss of life.
Japan is a nation with the most recorded tsunamis in the world. The earliest recorded
disaster being that of the 684 A.D. Hakuho Quake. The number of tsunamis in Japan totals
195 over a 1,313 year period, averaging one event every 6.7 years, the highest rate of
occurrence in the world. These waves have hit with such violent fury that entire towns have
been destroyed. In 1896 Sanriku, Japan, with a population of 20,000, suffered such a
devastating fate.
On December 26, 2004, an undersea earthquake measuring 9.0 on the Richter scale
occurred 160 km (100 mi) off the western coast of Sumatra, Indonesia. It was the fifth largest
earthquake in recorded history and generated massive tsunamis, which caused widespread
devastation when they hit land, leaving an estimated 250,000 people dead in countries around
the Indian Ocean.
The 2004 Indian Ocean earthquake, which had a magnitude of 9.3, triggered a series of
lethal tsunamis on December 26, 2004 that killed approximately 230,000 people (including
168,000 in Indonesia alone), making it the deadliest tsunami in recorded history. The tsunami
killed people over an area ranging from the immediate vicinity of the quake in Indonesia,
Thailand and the north-western coast of Malaysia to thousands of kilometres away in
Bangladesh, India, Sri Lanka, the Maldives, and even as far as Somalia, Kenya and Tanzania
in eastern Africa.
Unlike in the Pacific Ocean, there was no organized alert service covering the Indian
Ocean. This was in part due to the absence of major tsunami events since 1883 (the Krakatoa
314 Alexander Bolonkin
eruption, which killed 36,000 people). In light of the 2004 Indian Ocean tsunami, UNESCO
and other world bodies have called for a global tsunami monitoring system.
DESCRIPTION OF INNOVATION
Current coast-protection dams are built from solid material (heaped stones, concrete,
piled soil). They are expensive to emplace and, sometimes, are unsightly. Such dams require
detailed on-site research of the surface and sub-surface environment, costly construction and
high-quality building efforts over a long period of time (years). Naturally, the coast city
inhabitants lose the beautiful sea view and ship passengers are unable to admire the city
panorama of the partly hidden city (New Orleans, which is below sea level). The sea coastal
usually has a complex geomorphic configuration that greatly increases the length and cost of
dam protections.
Authors offer to protect seaport cities against hurricane storm surge waves, tsunamis, and
other weather related-coastal and river inundations by new special design of the water and
land textile dams.
The offered dam is shown in Figure 3a below. One contains the floats 4, textile (thin
film) 3 and support cables 5. The textile (film) is connected a top edge to the floats, the lower
edge to a sea bottom. In calm weather the floats are located on the sea surface (Figure 1a) or
at the sea bottom (Figure 1b). In stormy weather, hurricane, predicted tsunami the floats
automatically raise to top of wave and defend the city from any rapid increase of seawater
level (Figure 3c).
Figure 1. Protection city against hurricane storm surge waves, tsunamis, and other weather relatedcoastal
inundations by textile (film) membrane located in sea (ocean). (a) - position of membrane on a
sea surface in a calm weather; (b) - position of membrane on a sea bottom in a calm weather; (c) -
position of membrane in hurricane storm surge waves, tsunamis, and other weather related-coastal
inundations. Notations: 1 - city, 2 - sea (ocean), 3 - membrane, 4 - float, 5 - support cable, 6 -
connection of membrane to a sea bottom, 7 - connection of support cable to a sea bottom, 8 - sea
bottom, 9 - wind.
New Concepts, Ideas and Innovations in Aerospace… 315
This textile-based dam‘s cost-to-build is thousands of times cheaper then a massive concrete dam, and a
textile infrastructure may be assembled in few months instead of years! They may be installed on
ground surface around vital or important infrastructure objects (entries to subway tunnels, electricity
power plants, civic airport, and so on) or around a high-value part of the city (example, Manhattan
Island) if inundation poses a threat to the city (Figure 2). These textile protections are mobile and can
be relocated and installed in few days if hurricane is predictably moving to given city. They can defend
the noted object or city from stormy weather inundation, tsunamis, and large waves of height up 30 and
more feet.
Figure 2. Protection city against hurricane storm surge waves, tsunamis, and other weather relatedcoastal
inundations by textile (film) membrane located on ground surface. (a) - position of membrane
on a ground surface in a compact form in a calm weather; (b) - position of membrane in hurricane storm
surge waves, tsunamis, and other weather related-coastal inundations. Notations: 1 - city, 2 - membrane
in the compact form, 3 - support cable, 4 - membrane, 5 - float, 6 -water, 7 - connection of support
cable to a sea bottom.
The offered textile dam may be also used as a big source of electricity. They can be built
as the dams in rivers and it is used as water dams for the electric station (Figure 3).
They also can be used as the dams for an ebb - flow sea electric station (Figure 4).
Double textile dams can be also used for drying a big area of a shallow sea and
converting its to industrial and farmland zones or for connection of closely islands (Figure 5).
It may be cheaper then to build an expensive bridges or underground tunnels. For security the
textile dams must be double (Figure 5) and area located lower a sea level must be divided in
zones separated by additional membranes.
Figure 3. Textile dam and electric station in a river. (a) side view; (b) - top view.
Notations: 1 - textile dam, 2 - float, 3 - electric station, 4 - water flow.
316 Alexander Bolonkin
Figure 4. Tidal (ebb and flow) electric station with textile dam. (a) - ebb; (b) - flow.
Notations: 1 -textile membrane, 2 - float, 3 - electric station.
Figure 5. Ground connection between islands or converting a shallow sea in dry land by textile
membranes. Notations: 1 - the fist island, 2 - the second island, 3 - sea, 4 - double textile membrane, 5 -
textile partitions between the double membranes, 6 - additional emergency ground textile partition, 7 -
car (track) highway, 8 - railroad, 9 - dwelling (industrial) zone; 10 - farmland.
The membranes must be made from artificial fiber or a film. The many current artificial
fibers are cheap, have very high safety tensile stress (some times more the steel!) and
chemical stability. They can work as dam some tens years. They are easy for repair.
THEORY AND COMPUTATION
1. Force P [N/m2
] for 1 m2
of dam is
P g h
(1)
where g = 9.81 m/s2 is the Earth gravity; is water density, =1000 kg/m3; h is difference
between top and lower levels of water surfaces, m (see computation in Figure 6).
2. Water power N [W] is
1.5 N gmh, m vS, v 2gh, N g hS 2gh, N / S 43.453h
[kW/m2
]
(2)
where m is mass flow across 1 m width kg/m; v is water speed, m/s; S is turbine area, m2
; is
coefficient efficiency of the water turbine, N/S is specific power of water turbine, kW/m2
.
Computation is presented in Figure 7.
New Concepts, Ideas and Innovations in Aerospace… 317
Figure 6. Water pressure via difference of water levels.
Figure 7. Specific power of a water turbine via difference of water levels and turbine efficiency
coefficient.
3. Film thickness is
2
2
g h
(3)
318 Alexander Bolonkin
where is safety film tensile stress, N/m2
. Results of computation are in Figure 8. The
fibrous material (Fiber B, PRD-49) has σ = 312 kg/mm2
and specific gravity γ = 1.5 g/cm3
[7].
Figure 8. Film (textile) thickness via difference of water levels safety film (textile) tensile stress.
4. The film weight of 1m width is
Wf 1.2 H
(4)
Computation are in Figure 9. If our dam has long L m, we must multiple this results by L.
Figure 9. One meter film weight via the deep of dam and film thickness c, density 1800 kg/m3
.
New Concepts, Ideas and Innovations in Aerospace… 319
5. The diameter d of the support cable is
S
d
T
S
Pl T
4
, ,
2
2
(5)
where T is cable force, N; l2 is distance between cable, m; S is cross-section area, m2
.
Computation is presented in Figure 12. The total weight of support cable is
2 / , , Wc
cHSL l
2 Wa
cSL
(6)
where c
is cable density, kg/m3
; L is length of dam, m; Wa is additional (connection of banks)
cable, m. The cheap current fiber has σ = 620 kg/mm2
and specific gravity γ = 1.8 g/cm3
[7].
6. Maximum sea raise of water from hurricane versus wind speed is
2
2 V
h
(7)
where h is water raising, m; = 1.225 kg/m3
; V is wind speed, m/s; = 1000 kg/m3
is
water density. Computation is presented in Figure 11.
Figure 10. Diameter of the support cable via difference of a water levels and the safety tensile stress for
every 10 m textile dam.
Wind speed is main magnitude which influences in the water raising. The direction of
wind, rain, general atmospheric pressure, deep, and relief of sea bottom, Moon phase, also
influence to the water raising and can decreases or increases the local sea level computed by
Equation (7). For example, in hurricane "eye" the wind is absent, but atmospheric pressure is
very low and sea level is high.
320 Alexander Bolonkin
Figure 11. Raising of sea level via wind speed.
APPLICATION
Using the graphs above, we can estimate the relevant physical parameters of many
interesting macroprojects [1] - [6].
CONCLUSION
Author offered and researched the new method and cheap design the land and sea textile
(film) dams. The offered method of the protection of seaport cities against hurricane storm
surge waves, tsunamis, and other weather related inundations is cheapest and has the very
perspective applications for defense from natural weather disasters. That is also method for
producing a big amount of renewable cheap energy, getting a new land for sea (and non-sea)
countries. However, there are important details not considered in this research. It is
recommended the consulting with author for application this protection.
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: "Bolonkin", and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Bolonkin A.A., Cathcart R.B., Fabric Aerial Dams/Wind Turbines on Antarctica.
http://arxiv.org.
[2] Bolonkin A.A., Cathcart R.B., Inflatable 'Evergreen' Dome Settlements.
http://arxiv.org.
[3] Bolonkin A.A., Cathcart R.B., A Cable Transportation System at the Earth's Poles to
Support Exploration of the Moon Lunar Industries. JBIS, Vol. 59, pp.375-380, 2006.
New Concepts, Ideas and Innovations in Aerospace… 321
[4] Bolonkin A.A., Cathcart R.B.,The Java-Sumatra Aerial Mega-Tramway.
http://arxiv.org.
[5] Cathcart R.B., Bolonkin A.A., Ocean terracing, http://arxiv.org.
[6] Macro-Engineering: A Challenge for the Future. Collection of articles. Edited by
V.Badescu, R.B. Cathcart and R.D. Schulling, Springer, 2006.
New Concepts, Ideas and Innovations in Aerospace…
Chapter 6
A LOW-COST NATURAL GAS/FRESHWATER
AERIAL PIPELINE
ABSTRACT
Offered is a new type of low-cost aerial pipeline for delivery of natural gas, an
important industrial and residential fuel, and freshwater as well as other payloads over
long distances. The offered pipeline dramatically decreases the construction and
operation costs and the time necessary for pipeline construction. A dual-use type of
freight pipeline can improve an arid rural environment landscape and provide a reliable
energy supply for cities. Our aerial pipeline is a large, self-lofting flexible tube disposed
at high altitude. Presently, the term ―natural gas‖ lacks a precise technical definition, but
the main components of natural gas are methane, which has a specific weight less than
air. A lift force of one cubic meter of methane equals approximately 0.5 kg. The
lightweight film flexible pipeline can be located in the Earth-atmosphere at high altitude
and poses no threat to airplanes or the local environment. The authors also suggest using
lift force of this pipeline in tandem with wing devices for cheap shipment of a various
payloads (oil, coal and water) over long distances. The article contains a computed
macroproject in northwest China for delivery of 24 billion cubic meter of gas and 23
millions tonnes of water annually.
Keywords: self-lofting aerial pipeline, dual use pipeline, long-distance freight transport.
INTRODUCTION
Natural gas is a mixture of flammable gases, mainly the hydrocarbons methane (CH4) and
ethane that found in bulk beneath the Earth‘s surface. Helium is also found in relatively high
concentrations in natural gas. Natural gas usually occurs in close association with petroleum.
Although many natural gases can be used directly from the well without treatment, some must
be processed to remove such undesirable constituents as carbon dioxide, poisonous hydrogen
sulfide, and other sulfur components.
Methods of pipeline transportation that were developed in the 1920s marked a significant
stage in the use of gas. After World War II there occurred a period of tremendous expansion
that has continued into the 21st Century. Increasingly, this expansion relies on the use of
pipeline transportation of gas. Among the largest accumulations of natural gas are those of
Kept as paper by A. Bolonkin and R. Cathcart in http://Arxiv.org
324 Alexander Bolonkin
Urengoy in Siberia, the Texas Panhandle in the United States, Slochteren-Groningen area in
The Netherlands, and Hassi RMel in Algeria. Gas accumulations are mostly encountered in
the deeper parts of sedimentary basins. Natural gas fields are often located far from the major
centers of consumption. Consequently, the gas must be transported. Transportation of natural
gas depends upon its form. In a gaseous form it is transported by pipeline under high
pressure, and in a liquid form it is transported by tanker ship [1].
Tipical ground pipeline
Large gas pipelines enable gas to be transported over great distances. Examples are the
North American pipelines, which extend from Texas and Louisiana to the Northeast coast,
and from the Alberta fields to the Atlantic seaboard. Transportation pressure is generally 70
kilograms per square centimeter (up to 200 atm) because transportation costs are lowest for
pressures in this range. Natural gas pipeline diameters for such long-distance transportation
have tended to increase from an average of about 60 to 70 centimeters in 1960 to about 1.20
meters nowadays. Some macroprojects involve diameters of more than 2 meters. Because of
pressure losses, the pressure is boosted every 80 or 100 kilometers to keep a constant rate of
flow.
Petroleum prospecting has revealed the presence of large gas fields in Africa, the Middle
East, Alaska, and China. Gas is transported from developed regions by special LNG ships.
The gas is liquefied to –160 C and transported in tankers with insulated containers. Since
1965 the capacity of tankers has risen to as much as 120,000 cubic meters, which enables
some tankers to convey as much as 70 million cubic meters of gas per voyage. Land or seabased
storage of low-temperature liquefied gas requires double-walled tanks with special
insulation. Such tanks may hold as much as 50,000 cubic meters. Even larger storage
facilities have been created by using depleted subsurface oil or gas geological reservoirs near
consumption centers or by the creation of artificial gas fields in aquifer layers. The latter
technique developed rapidly, and the number of storage facilities of this type in the USA
New Concepts, Ideas and Innovations in Aerospace… 325
increased tremendously during the late 20th Century. There are also such underground storage
areas in France and Germany.
Tube pipeline in polar regions.
Residential and commercial use consumes the largest proportion of natural gas in North
America and Western Europe, while industry consumes the next largest amount and electricpower
generation is third in worldwide natural-gas consumption. By far the major use of
natural gas is as fuel, though increasing amounts are used by the chemical industry for raw
material. Among the industries that consume large volumes are food, paper, chemicals,
petroleum refining, and primary metals. In the USA, a large amount fuels household heaters;
in Russia a considerable volume goes for electric-power generation and to generate export
revenue. Exportation and importation of natural gas involves some aspects of geopolitical
assessment [2]
Most materials that can be moved in large quantities in the form of liquids, gases, or
slurries (fine particles suspended in liquid) are generally moved through freight pipelines [3].
Pipelines are lines of pipe equipped with pumps, valves, and other control devices for
transporting materials from their remote sources to storage tanks or refineries and in turn to
distribution facilities; pipelines may also convey industrial waste and sewage to processing
plants for treatment before disposal.
Pipelines vary in diameter from tiny pipes up to lines 9 meters across used in highvolume
freshwater distribution and sewage collection networks. Pipelines usually consist of
sections of pipe made of steel, cast iron, or aluminum, though some are constructed of
326 Alexander Bolonkin
concrete, fired clay products, and occasionally plastics. The sections are joined together and,
in most cases, installed underground. Because great quantities of often expensive and
sometimes environmentally harmful materials are carried by pipelines, it is essential that the
systems be well constructed and monitored in order to ensure that they will operate smoothly,
efficiently, and safely. Pipes are often covered with a protective coating of coal-tar enamel,
asphalt, or plastic; sometimes these coatings may be reinforced or supplemented by an
additional sheath of asbestos felt, fiberglass or polyurethane. The materials used depend on
the substance to be carried and its chemical activity and possible corrosive action on the pipe.
Pipeline designers must also consider such factors as the capacity of the pipeline, internal and
external pressures affecting the pipeline, water- and air-tightness, and construction and
operating costs. Generally the first step in construction is to clear the ground and dig a trench
deep enough to allow for approximately 51 centimeters of soil overburden to cover the pipe.
Sections of pipe are then held over the trench, where they are joined together by welding,
riveting or mechanical coupling, covered with a protective coating, and lowered into position.
Pipelines of some water-supply systems may follow the slope of the land, winding through
irregular landscapes like low-gradient railroads and highways do, and rely on gravity to keep
the water flowing through them. If necessary, the gravity flow is supplemented by pumping.
Most pipelines, however, are operated under pressure to overcome friction within the pipe
and differences in elevation. Such systems have a series of pumping stations that are located
at intervals of from 80 to 320 kilometers. Many pipelines are equipped with a system of
valves that may be shut in the event of a breach in the line. Nevertheless, a short-period
breach could still result in a spill of oil or escapes of gas. Vigilant ground and air inspection
crews help to avert such damaging and costly accidents by checking periodically the pipeline
for obvious weaknesses and stresses. Various methods are used to control corrosion in
metallic pipelines. It is worth noting that metallic pipelines, especially those located on the
Earth‘s surface, are subject to Space Weather, just like electric power grids [4]. In cathodic
protection, a negative electrical charge is maintained throughout the pipe to inhibit the
electrochemical process of corrosion. In other cases the interior is lined with paints and
coatings of plastic and rubber or wrappings of fiberglass, asphalt, or felt. Sometimes
corrosion-inhibiting chemicals are injected into the cargo. Pipelines are also cleaned by
passing devices called pigs; a pig may be a ball of the same diameter as the pipe; this kind of
pig works by scraping clean the pipe's interior as it is propelled along by the flowing cargo. It
may also be a complex scrubbing machine that is inserted into the pipe through a special
opening. One of the longest metallic gas pipelines in the world is the Northern Lights
pipeline, which is 5,470 kilometers long and links the West Siberian gas fields on the Arctic
Circle with locations in Eastern Europe; in China, the recently completed ―West Gas
Supplying To East Project‖, yearly conveys 12 trillion cubic meters of natural gas from
Xijiang Province gas fields to Beijing, the capital, in a 4,000 kilometer-long metallic pipeline.
The main differences of suggested Gas Transportation Method and Installation from
modern metallic pipelines are:
(1) The tubes are made from a lightweight flexible thin film (no steel or solid rigid hard
material).
(2) The gas pressure in tube equals an atmospheric pressure of 1- 2 atm. (Some current
gas pipelines have pressure of 70 atm.).
New Concepts, Ideas and Innovations in Aerospace… 327
(3) Most of the filmic pipeline [except compressor (pumping) and driver stations] is
located in the Earth-atmosphere at a high altitude (0.1-6 km) and does not have a
rigid support (pillar, pylon, tower). All operating pipelines are located on the ground
surface, underground or underwater.
(4) The transported natural gas supports the air pipeline in the air above the route
selected.
(5) Additional aerial support may be made by employment of attached winged devices.
(6) The natural gas pipeline can be used as an air transport system for oil and solid
payloads with a maximum speed up of 250 m/sec.
(7) The natural gas pipeline can be used as a transfer of a mechanical energy.
The suggested Method and Installation have remarkable cost-benefit advantages in
comparison with all existing natural gas pipelines.
DESCRIPTION OF INNOVATION
A gas and payload delivery gas/load pipeline is shown on figures 1 - 5.
Figure 1 shows the gas/load delivery installation by air pipeline.
The installation works in the following manner: The compressor station pumps natural
gas from storage into the tube (pipeline). The tube is made from light strong flexible gasimpermeable
fireproof material (film), for example, from composed material (fibers,
whiskers, nanotubes, etc.). A gas pressure is a less than an atmospheric pressure (up 1-2 atm).
A natural (fuel) gas has methane as its main component with a specific density about 0.72
kg/m3
. Air has a specific density about 1.225 kg/cubic meter. That means that every cubic
meter of gas (methane) or a gas mixture has a lift force approximately 0.5 kg. The linear (one
meter) weight of a tube is less than a linear lift force of gas into the tube and the pipeline,
therefore, has a lift force. The pipeline rises up and steadies at a given altitude (0.1 - 6 km),
held fast by the tensile elements 3. The altitude of the aerial pipeline can be changed by the
use of common winches 7. The compressor station is located on the ground surface and
moves natural gas to the next compressor station that is ordinarily located at the distance 70 -
250 km from previous compressor station. Inside of the aerial pipeline there are valves
(Figure 4) dedicated to lock the tube tightly in case of it is punctured, ruptured or otherwise
damaged. The pipeline has also the warning light indicator 5 for aircraft.
Figure 1. General view of aerial pipeline between two compression (pump) stations. (a) Side view, (b)
front view. Notations: 1 - pipeline in atmosphere, 2 - compression station, 3 - tensile stress element, 4 -
supportive wing device, 5 - night light, 6 - load (container) monorail, 7 - winch.
The route selected for our example—see below—is well north of IATA-1, the new
International Air Transport Association-approved flight-path for airliners coming from, or
going to Europe via Hong Kong or Shanghai. Only international flights arriving or departing
328 Alexander Bolonkin
Beijing might come close to the selected example. Even if hit by an airliner, if the aircraft
speed is greater than about 3% of the stress wave velocity, or greater than about 150 m/sec,
the airplane‘s speed causes an immediate fracture that is independent of cable diameter,
although the force on the vehicle‘s wing certainly is not! Figure 2 shows the gross-section of
the gas pipeline and support ring. The light rigid tube ring keeps the lift force from gas tube,
wing support devices, from monorail and load container.
Figure 2. Gross-section and support ring of aerial natural gas pipeline. (a) front view, (b) side view.
Notations: 9 - double casing, 10 -rigid ring, 11 - monorail, 12 - wing load container, 13 - rollers of a
load container, 14 - thrust cable of container, 15 - container wing. Other notations are same Figure 1.
Figure 2a. Front view of the winged load container, monorail, and suspension bracket. Other notations
are same figures 1-2.
Figure 3 shows the compressor (pumping) station. The station is located on the ground
and works in the following way. The engine 32 rotates compressor 31. That may be propellers
located into rigid bogy connected to the flexible tubes of installation 1. The tubes are located
at atmosphere. The propellers move the gas in given direction.
New Concepts, Ideas and Innovations in Aerospace… 329
Figure 3. Compression (pump) station. Notations: 31 - compressor (propeller), 32 - engine. Other
notations are same figures 1-3.
Figure 4 shows two variants a gas valve. The fist valve version is an inflatable boll. The
ball fill out and closed the gas way. The second version is con conventional light flat choker
in a form of circle. The valve works in the following way. When the tube section is damaged,
the pressure decreases in a section. The control devices measure it and, subsequently, the
valves close the pipeline. The valve control devices have a connection with a central
dispatcher, who can close or open any sub-section of the very long proposed natural gas
pipeline.
Figure 4a shows the spherical valve (a ball) in a packed form. Figure4b shows the
spherical valve (a ball) in an open form. The tubes of pipeline have a double wall (films) and
gas streak between them. If the walls damage the streak gas flows out and the second film
closes the hole in the first film and save a tube gas.
Figure 4. Gas valve. (a)-(b) Inflatable valve, (c)-(d) Flat valve. Notations: 40 - inflatable valve in
compact position, 41 - inflatable valve in fill out position, 42 - gas flow, 43 - gas pressure, 44 - flat
choker.
The winged device 4 is a special automatic wing feature. When there is windy weather
and the side wind produces a strong side force, the winged devices produce a strong lift force
and support pipeline in fixed vertical position.
330 Alexander Bolonkin
The winged device works in the following way: when there is a side wind the tube has the
wing drag and the winged device creates needed additional lift force. All forces (lifts, drags,
weights) are in equilibrium. The distance between the tensile elements 3 is such that the tube
can resist the maximum storm wind speed. The system can have a compensation ring. The
compensation ring includes ring, elastic element, and cover. The ring compensates the
temperature‘s change of the tube and decreases a stress from a wind.
The suggested gas pipeline has big advantages over the conventional steel gas pipeline:
(1) The suggested natural gas pipeline is to be made from a thin film that is hundreds of
times less expensive than current gas pipelines currently made from steel tubes.
(2) Construction time might be decreased from years to a few months.
(3) There is no need to compress a gas, a huge saving of energy and expenditures for
high-maintenance pumps.
(4) No need for expensive ground surface and environmental damage during either the
building or exploitation phases of the macroproject.
(5) No environmental damage in case of pipeline‘s damage during use.
(6) Easy to repair.
(7) Decreasing energy for delivery.
(8) Additional possibility of payload delivery in both directions.
(9) If the aerial natural gas pipeline is situated at high altitude, it is more difficult for
successful terrorist attacks and for gas thefts.
(10)The suggested transportation system may be also used for a transfer of mechanical
energy from one driver station to another.
More detail description of innovation the reader finds in publication. See [5]-[8].
Below, the authors have computed a macroproject suitable for Beijing region and the
desert located in China‘s northwest territory. In addition, the authors have also solved
additional problems, which appear in this and other macroprojects and which can appear as
difficult as the proposed pipeline and transportation system itself. (The authors are prepared
to discuss the technical problems with serious organizations that are interested in researching
and developing these ideas and related macroprojects.)
METHODS OF THE ESTIMATION OF THE ALTITUDE
GAS PIPELINE
1. Gas delivery capability is
G = D
2
V/4 [m3
/sec], (1)
where: D is diameter of tube [m];
V is average gas speed [m/sec].
2. Increment pressure [N/m2
] is
P = L V
2
/2D , (2)
New Concepts, Ideas and Innovations in Aerospace… 331
where: is dimensionless factor depending on the wall roughness, the fluid properties, on the
velocity, and pipe diameter ( = 0.01 - 0.06); L is the length [m]; is fluid density [kg/m3
].
3. The dimensionless factor can be taken from graph [5, p. 624]. It is
= f(R,) , (3)
where: R = V D/ is Reynolds number, is fluid viscosity; is measure of the absolute
roughness of tube wall.
4. Lift force F of the one meter length of pipeline is
F = (a - m)v , (4)
where: a = 1.225 kg/m3
is air density for standard atmosphere; m = 0.72 kg/m3
is methane
density; v = D
2
/4 is volume of one meter length of pipeline.
5. Needed thickness of tube wall is
= PD/2 , (5)
where: P is pressure [see Eq.(2)]; is safety stress. That is equals 100 - 200 kg/mm2
for
matter from current artificial fiber.
6. Weight of one meter pipeline is
W = D , (6)
where: is specific weight of tube matter (film, cover). That equals about 0.9 - 2.2 kg/m3
for
matter from artificial fiber.
7. Air drag D of pipeline from side wind is
D = Cd V
2
S/2 , (7)
where: Cd is drag coefficient; S is logistical pipeline area between tensile elements; is air
density.
8. Needed power for delivery is
N = PG/ , (8)
where: 0.9 is a efficiency coefficient of a compressor station.
Load Transportation System under Pipeline
1. Load delivery capability by wingless container is
332 Alexander Bolonkin
Gp = k F Vp , (9)
where: k is load coefficient (k 0.5 < 1); Vp is speed of container (load).
2. Friction force of wingless containers (rollers) is
Fc = f Wc
, (10)
where: f 0.03 - 0.05 is coefficient of roller friction; Wc
is weight of container between
driver stations.
3. Air drug of container is
Dc = CcV
2
Sc
/2 , (11)
where: Cc
is drug friction coefficient related to Sc
; Sc
is cross-section area of container.
4. The lift force of a wing container is
cw
a
c L cw L S
V
L C qS C
2
2
,
(12)
where: CL 1 1.5 is coefficient of lift force;
/ 2
2
q aV
is air dynamic pressure, N/m2
;
Scw is wing area of container, m2
.
5. The drug of wing container may be computed by equation
D
L
cw
a
C L cw L
C
C
S K
K
V
D C qS K C , where
2
/
2
(13)
where K 10 20 is coefficient of aerodynamic efficiency; CD is air drag coefficient of wing
container. If lift force of wing container equals the container weight, the friction force F is
absent and not necessary in monorail.
6. The delivery (load) capacity of the wing container is
d
WV T
G
c
c
1
(14)
where W1 is weight of one container, kg; Vc = 30 200 m/s is container speed, m/s; T is time,
s; d is distance between two containers, m.
7. The lift and drag of the wing device may be computed by Equations (12)-(13). The power
needs for transportation system of wing container is
New Concepts, Ideas and Innovations in Aerospace… 333
c
c
c
K
gWV
P
(15)
where W is total weight of containers, kg; g = 9.81 m/s2
is Earth gravity; Kc 10 20 is
aerodynamic efficiency coefficient of container and thrust cable;
8. The stability of the pipeline against a side storm wind may be estimated by inequality
tan 0
/
T d d
T d T S
D L K
L L gW gW A
(16)
where LT is lift force of given part of pipe line (conventionally it is distance between the
tensile element, N; Ld is lift force of wing device, N; WT is a weight of pipeline of given part,
kg; Ws
is weight of the given part suspending system (containers, monorail, thrust cable,
tensile element, rigid ring, etc.), kg; DT is drag of the given part of pipeline, N; Ld is the lift
force of the wing device, N; Kd is an aerodynamic efficiency coefficient of wing device; is
angle between tensile element and ground surface.
CHINA GAS/WATER AERIAL PIPELINE MACROPROJECT
(Tube diameter equals D = 10 m, gas pipeline has the suspension load transport system,
the project is suitable for Beijing region –Gobi Desert)
Let us take the distance between the compressor-driver stations 100 km and a gas speed
V = 10 m/sec.
Gas delivery capacity is (Eq. (1))
G = D
2V/4 = 800 m3
/s = 24 billions m3
per year.
For the Reynolds number R = 107
value is 0.015, P = 0.18 atm (Eq. (2)-(3)). We can
take V = 20 m/s and decrease delivery capacity by two (or more) times.
Lift force (Eq.4) of one meter pipeline‘s length equals F = 39 kg.
We take the thickness of wall as 0.15 mm for = 200 kg/sq. mm.
The cover weight of one-meter pipeline‘s length is 7 kg. The needed power of the
compressor station (located at distance 100 km) equals N = 10,890 kW for = 0.9.
LOAD TRANSPORTATION SYSTEM
Let us take the speed of delivery equals V = 30 m/sec, payload capability is 20 - 25 kg per
one meter of pipeline in one direction. Then the delivery capability for non-wing containers is
750 kg/s or 23 millions tons per year.
That is more than gas delivery (18 million tons per year). The total load weight
suspended under the pipeline of length L = 100 km equals 2500 tons. If a friction coefficient
is f = 0.03, the needed trust is 75 tons and needed power from only a friction roller drug is N1
= 22,500 kW (Eq. (10)).
334 Alexander Bolonkin
If the air drag coefficient Cd = 0.1, cross section container area Sc = 0.2 m2
, the air drag of
a one container equals Dc1 = 2.2 kg, and total drag 20,000 container of length 100 km is Dc =
44 tons. The need driver power is N2 = 13,200 kW. The total power of transportation system
is N = 22500 + 13200 = 35,700 kW. The total trust force is 77 + 44 = 121 tons.
If = 200 kg/sq. mm, the cable diameter equals 30 mm.
The suggested delivery system can delivery a weight units (non-wing container) up to
100 kg if a selected length of container is 5 - 7.5 m.
The pipeline and container delivery capability may be increased at tens of times if winged
containers are utilized. In this case we are not limited in load capability. Winged container
needs a very lightweight monorail (or without it) and only in closed-loop thrust cable. That
can be used for delivery water, oil or payload in containers. For example, if our system
deliveries 4 m3
/second that is equivalent of a normal river (or a water irrigation canal) having
a cross-section area equal to 202 m and water flowing speed 0.1 m/s. In other words,
northwest China‘s planted desert dust suppression macroproject—the Great Green Wall [9]—
can be fostered by delivery of irrigation water to the vegetation that may become available in
AD 2008, just as the Olympic Games are played in Beijing, from the East Route of the
―South-North Water Transfer Scheme‖ [10].
This particular macroproject system can transfer mechanical energy, we can transfer
35,700 kW for the cable speed at 30 m/sec, and 8 times more by the same cable having a
speed 250 m/sec.
If the < 60o
and wing of winged device has a width of 6 m, the system is stable against
a side-thrusting storm wind of 30 - 40 m/second.
REFERENCES
(Reader can find part of these articles in WEBs: http://Bolonkin.narod.ru/p65.htm,
http://arxiv.org, search: "Bolonkin", and in the book "Non-Rocket Space Launch and Flight",
Elsevier, London, 2006, 488 pgs.)
[1] Craig Hooper, ―The Peril of Power: Navigating the Natural Gas Infrastructure‖,
Proceedings of the US Naval Academy 132: 40-44 (June 2006).
[2] David G. Victor, A.M. Jaffe and M.H. Hayes, Natural Gas and Geopolitics: From 1970
to 2040 (Cambridge University Press, NY, 2006) 487 pages.
[3] Mohammad Najafi (Ed.) Pipelines 2003: New Pipeline Technologies, Security, and
Safety: International Conference on Pipeline Engineering and Construction 2003, 13-16
July 2003, Baltimore, Maryland, USA.
[4] John G. Kappenman, ―The Evolving Vulnerability of Electric Power Grids‖, Space
Weather Quarterly 2: 10-12 (Spring 2004).
[5] Bolonkin A.A., Patent Application "Method for Gas and Payload Transportation at
Long Distance and Installations for It", USPTO # 09/978,507.
[6] Bolonkin A.A., Patent Application "Method Transportation of Vehicles and
Installations for It", USPTO # 09/893,060.
[7] Bolonkin A.A., Air Cable Transport System, Journal of Aircraft 30: 265-269 (MarchApril
2003)
New Concepts, Ideas and Innovations in Aerospace… 335
[8] Bolonkin A.A., Non-Rocket Space Launch and Flight (Elsevier, London, 2006), 488
pages.
[9] Caroline Williams, ―A land turned to dust‖, New Scientist 186: 38-41 (4 June 2005).
[10] Richard Stone and Hawk Jia, ―Going Against the Flow‖, Science 313: 1034-1037 (25
August 2006).
New Concepts, Ideas and Innovations in Aerospace…
Chapter 7
AIR OBSERVE SYSTEM
ABSTRACT
This manuscript contains a description and basic principles for observing
inaccessible areas using low cost, easily deployed equipment. The basic premise is to
suspend a tiny video camera at an altitude of 10 - 200 meters over the area to be
surveyed. The TV camera supports at altitude by wind or balloon. The technical
challenges regard the means by which the camera is suspended. Such a system may be
used by military or police forces or by civil authorities for rescue missions or assessment
of natural disasters. The method may be further developed for military applications by
integrating the surveillance task with deployment of munitions.
Keywords: air observer, air suspended system, low altitude video observer.
1.INTRODUCTION
1.1. Historical Perspective
From 1993-2000 the Defense Advanced Research Projects Agency (DARPA) spent 35
millions dollars for Micro Air Vehicle (MAV) research. Micro aircraft, no larger than a small
bird, are already showing promise in reconnaissance roles by flying with video cameras and
returning live pictures. At present time the Air Force and Army continue Micro Air Vehicle
(MAVs) research and development for assisting ground soldiers with non-line-of-sight
reconnaissance. Unfortunately, after 10 years of development and spending hundreds of
millions of dollars, we still do not have a MAV suitable for reliable, sustainable close-in
surveillance. The reason is that the MAV method is fundamentally limited for this role. It is
impossible to use when the wind is strong. As fuel capacity is limited, observation times are
very limited. An enemy can fairly easily see and avoid (or destroy) the MAV because the
MAV must flights at low altitude when using small, lightweight cameras and optics. The
Presented as paper AIAA-2006-6511 to Atmospheric and Flight Mechanic Conference, 21-24 August, 2006,
Keystone, USA.
338 Alexander Bolonkin
soldier may require special training for control and operation of the MAV, especially if it
does not have an autopilot.
We propose have a method based upon a simple device, which does not have these
shortcomings and in some cases, may be more efficient than a MAV.
1.2. Short Description of the Micro Air Observer (MAO)
The basic approach for this method is to suspend a very small, essentially invisible,
Micro Air Observer (MAO) or (SAO) - Suspended Air System at a controlled altitude over an
area to be investigated. The MAO device includes: (1) aerial support device (kite, air balloon)
located at a relatively high altitude (e.g. 1000 m) which is connected by a thin fiber cable and
thin electric wire to anchors (and a battery) located at the Earth‘s surface; (2) a micro video
camera (and microphone) at the low altitude (100-200 m) connected to the support device by
thin fiber cable and wire; (3) support electronics including a transceiver, radio control, and
small battery; (4) control and observation ground station for the soldier (or operator).
Optionally, the MAO may also contain a self-destructor. The entire device may be packaged
in a canister and dispensed from an aircraft or artillery shell. Most of the devices required to
build the MAO exist off-the-shelf and have a combined weight 20-90 grams and volume of
10-50 cubic centimeters.
There are several possible launch methods and conditions for the MAO:
a) The MAO is launched from aircraft. The aircraft dispenses the MAO canister into a
given area (Figure 1). The canister is opened at a given altitude, the kite (balloon) is
opened, the anchor falls on the ground and stabilizes the kite (balloon). The kite
deploys the camera to the desired altitude and begins operation. The kite may require
additional anchors (Figure 2) to ensure that the MAO will have the same position for
any wind direction. The schematic design of the canister and anchor are shown in
figures 3 and 4 respectively. Figure 5 show the MAO being launched from an air
launched cruise missile.
b) An artillery shell launches the MAO. When the shell flies at an altitude 100-200
meters, the support device (parachute) is opened If prevailing wind blows towards
enemy. The MAO may be operated as a kite as long as the wind speed remains never
drops below some threshold value for more than some determinable period of time.
c) and the MAO is braked (Figure 6). When the MAO reaches the ground, it is would
likely be self-destroyed by a flight termination unit.
d) If prevailing wind blows towards operator. The operator deploys the MAO in the
direction of the desired site. At the apogee of the trajectory the brake parachute is
opened, the MAO, connected to the shell by fiber, is slowed. The shell continues on
its trajectory and falls behind the enemy location. The shell is used as anchor for the
MAO (Figure 8) which flies as a kite, lowers the camera, and permanently observes
the enemy location.
e) If prevailing wind is orthogonal to line of sight between operator and observation
site. The MAO is deployed in an orthogonal direction (Figure9) and is configured as
in (d).
New Concepts, Ideas and Innovations in Aerospace… 339
Figure 1. Launching of MAO (SAO) from aircraft.
Figure 2. Launching of four anchor fixed SAO from aircraft.
340 Alexander Bolonkin
Figure 3. Canister for MAO (SAO).
Figure 4. Anchor. D – anchor in set up form.
New Concepts, Ideas and Innovations in Aerospace… 341
Figure 5. Launching of MAO (SAO) from missile or projectile.
Figure 6. Suspended Aerial Observer MAO (SAO).
Figure 7. Launching Micro Air Eye (MAE) as kite.
342 Alexander Bolonkin
Figure 8. Using MAO (SAO) when wind is from enemy.
Figure 9. Using MAO (SAO) when wind is from side (top view).
f) The camera fiber may be connected to the kite assembly via a controlled roller
(Figure10). It is moved along the main cable and changes position and altitude. The
MAO and/or camera assembly may also have a small vertical wing to increase
stability and to allow maneuver for increasing the observable area (Figure11).
Figure10. MAO with mobile TV camera.
New Concepts, Ideas and Innovations in Aerospace… 343
Figure 11. MAO observe area.
g) The MAO may be also suspended by an air balloon (diameter 1-1,5 foot, 25-40
cm)(Figure 12). In this case, it may operate in windless weather. Of course the
balloon would be easy to observe.
Figure 12. Support balloon: a) without wing; b) with wing.
h) For more efficiency or to permanently observe a large area, the MAO may be
connected to three to eight anchors (figures 13-14). In this case the MAO position
does not depend on wind direction.
344 Alexander Bolonkin
Figure 13. Installation for Stationary observe area: (A ) with balloon, (B) with wing.
Figure 14. Top view of the Installation of Figure7. A – three conventional cables, B – four
conventional cables, C – eight cables.
i) The support device or kite may have a sail form (Figure 15) or conventional airplane
form (it is most efficient, Figure 16). It must have control surfaces to control the
MAO. The camera assembly itself may have a small vertical wing and flaps (figures
17), which allows it to move side to side and back and forth. The spool also allows
changing the camera altitude and the flaps allow the operator to change the fiber
angle.
Figure 15. Support sail of MAO.
New Concepts, Ideas and Innovations in Aerospace… 345
Figure 16. Base wing.
Figure 17. Control position of TV camera.
j) The closed loop stabilization and pointing of the camera assembly will require a gyro
wind propeller (figures 18-19). The high revolution wind propeller has loads at the
blade ends (Figure 19). One has a rigid connection to the camera station, and a
346 Alexander Bolonkin
swivel-spring connection with the vertical wing. The gyro propeller has a gyroscopic
effect, which does not allow a sharp turn of the video cameras.
Figure 18. Fly apparatus with wind or electric gyro and stabilized TY camera.
Figure 19. Wind gyro stabilizer.
k) The camera assembly may have the two video cameras (Figure20): a widely angle
fixed lens and a narrow angle swinging mobile camera. The widely angle camera
allows the operator to observe a general picture, the narrow angle camera allows the
operator to observe a small selected object.
If the wind at low altitude is small or absent, the camera assembly may have a small
electric motor which rotates a gyro propeller (Figure20) which move the camera. The
propeller (Figure18b) can also rotate a small electric generator to power-up the electronics.
New Concepts, Ideas and Innovations in Aerospace… 347
Figure 20. Two cameras stabilized video station.
An auto-gyro propeller (diameter35-75 cm) (Figure 21) can be used as a support device.
It may also be rotated by its motor or a ground driver (motor) through a cable transfer (Figure
22).
Figure 21. Suspended Aerial Observer with passive autogiro propeller.
Figure 22. Suspended Aerial Observer with active propeller.
348 Alexander Bolonkin
The last variants are presented in figures 23-26. In Figure 23, the MAO uses an air
balloon, a mobile controlled suspended video camera and a control suspended fiber. The air
balloon (size 40-120 cm) is made from glass thin film, one is located at high altitude (200-500
m) and it only slightly visible from the surface. Figure 24 is the same as Figure 23, but the
MAO uses the propeller and motor as the support device. Figures 25-26 show the control
support device being used to increase the observed area.
Figure 23. Using of balloon MAO when no wind.
Figure 24. Using of propeller MAO when no wind.
Figure 25. Using of control balloon MAO when no wind.
New Concepts, Ideas and Innovations in Aerospace… 349
Figure 26. Using cont.propeller MAO when no wind.
Figure 27. Air Observer and Annihilator (AOA).
We can also use a small mobile controlled dirigible or helicopter. Our innovation is a
connection to them by thin fiber a small mobile controlled video camera (and microphone)
and lower them to an observe area or an enemy location. The main apparatus flies at high
altitude; the video camera suspends at low altitude and permanently observes a needed area.
350 Alexander Bolonkin
Figure 28. Load deliverer to AOA. A- side view; B-front view; C- Descent of Louder.
1.3. Advantages of Micro Air Observer in Comparison with Micro Air Vehicle
1. The suggested method may be applied in wind and weather when the MAV cannot
be used because the wind is strong, turbulence, has scuds and twirls from building
and trees. Indeed, to some extent, the greater the wind the better the performance of
the MAO. Examining worldwide wind profiles, the probability of being able to use
the MAO is greater than the probability of using a MAV. For example, for the
average annual wind speed 6 m/sec the probability of MAO launching (V minimum
3 m/sec) is 0.85 when the launch is made from ground (from aircraft it is more 0.9);
for MAV with maximum admissible speed 8 m/sec, the probability is only 0.65.
2. The offered method allows permanently observing a large area (some sq. km) a long
time (up to months). The current MAV can observe about 0.1 sq. km a short time (2-
5 min).
3. The offered method has power located on the ground and it can transmits the video
and control signals a long distance (up to hundreds km). The MAO or MAO can have
a small electric generator, which is rotated by the wind propeller, and thus the
devices (video camera and control) can operate a long time.
4. The suggested method allows permanently observing inside building rooms through
the building windows.
5. Apparatus may be deployed quickly.
6. The MAO control is simple and does not require special training to control - unlike a
micro air vehicle. Fitting a MAV with an autopilot is difficult and when completed
still requires the MAV to carry along additional power to persevere.
7. Both the MAO and MAV may be deployed from aircraft or artillery shells.
8. The MAO is simpler and less expensive than a MAV.
New Concepts, Ideas and Innovations in Aerospace… 351
1.4. Lack of Wind
The MAO can only operate if the wind (at altitude) is more than some certain minimum
(e.g. 2-3 m/sec). If the wind speed is less the minimum and MAO has special design, the
MAO will land but can take off again when wind speed again becomes high enough to launch
it. The MAO can also have a support air balloon. Special rotor kite can be supported by
ground engine in windless weather.
Of course the logical approach is use the MAO to supplement the MAV and vice versa.
The MAV and MAO have different conditions for application: the MAV in windless weather,
MAO in wind weather.
1.5. Summary
The MAO is launched from an aircraft or is launched via an artillery shell or gun into an
enemy observation area. As it enters a predetermined altitude 100-200 meters, the support
devise is opened, the MAO is braked, the anchor (attached to MAO by fiber) is dropped down
and connects the MAO to the ground (figures1-10). The support device may be a small (less
the one foot, 20-35 cm diameter) air balloon or small solid or inflatable kite or wing. The
connection fiber also is invisible from a short distance (1-3 meter) because it may be
fashioned very thin (as a hair) and is made from transparent and strong artificial material. If
there is a small wind (at most places the wind is 80-90% days in year at ground, see a
research below) the MAO will be supported at altitude by a small wing or wing sail (figures
5-9, 15). In other case, one can be supported a special MAO having a balloon with an
inflatable kite or wing (Figure 12-13). The support device (kite or wing) may be located at
high altitude (1 or more km, different from MAO) and be connected to MAO by a thin fiber.
There is sufficient wind at these high altitude about 95-98% of the year. Of course a major
benefit is that the batteries can be located on the ground and so the MAO can operate for a
long time. The MAO can also have a long antenna located at a high altitude and transmit a
video and control signal for quite some distance.
The operator can observe the area of interest for a very long time (even weeks). If it is not
needed in observation and no enemy, the soldier can reel it in up to the anchor (the anchor
must have a radio-locator) and reel the thread (fiber) and get his device back. The MAO can
be also launched as conventional kite for observe nearest closed area, especially, if the wind
blows in enemy side.
The offered method and MAO has the following advantages in comparison of MAV:
1. No needs for developing a new top technology, which can confine Research,
Development, and Design (as Micro engine, flight control, micro aerodynamics,
autopilot, and navigation system).
2. The cost of Research and Development (RandD), design of MAO is less in 10 times
that MAV.
3. The time of reconnaissance (observation) increases from 2-10 min to several weeks.
The signals can be transmitted to long distance.
4. The using and control of MAO are simpler than MAV (not necessary in special
training for soldiers or autopilot).
352 Alexander Bolonkin
5. MAO can be used in wind and bad whether.
6. MAO uses the video devices, radio control, and communication developed for MAV.
7. MAO is cheaper then MAV and can be RandD and manufactured in short time.
8. MAO may be invisible for enemy.
9. There are a permanently air flow at high altitude
Table 1. The MAO data with comparison future MAV data
1.6. Additional Possibility for Support MAO (SAO)
High altitude wind has another important advantage. It is stable and constant. This is true
practically everywhere.
Especially in the troposphere and stratosphere, the wind currents are powerful and
permanent. For example, at an altitude of 5 km, the average wind speed is about 20 M/s, at
altitude 10-12 km it may reach 40 m/s (at latitude of about 20-350N).
There are permanent jet streams at high altitude. For example, at H = 12-13 km and about
250N latitude. The average wind speed at the it core is about 148 km/h. The most intensive
portion, with a maximum speed 185 km/h latitude 220
, and 151 km/h at latitude 350
in North
America. On a given winter day speeds in the jet core may exceed 370 km/h for a distance of
several hundred miles along the direction of the wind. Lateral wind shears in the direction
normal to the jet stream may be 185 km/h per 556 km to right and 185 km/h per 185 km to
the left.
Reference: Science and Technolody,v.2, p.265.
2. THEORY AND COMPUTATION OF MAO (SAO)
2.1. Wind (Speed, Duration, Altitude Distribution, Speed Distribution)
Wind is important element of the offered method. In MAV the wind is only obstacle
which gives trouble for operator. The wind vortexes from buildings and trees are located at
near Earth surface. One can set down to MAV to a ground. If wind is more then 6-8 m/sec,
the flight of MAV can be impossible. In the MAO the wind is necessary for support of the
apparatus. If wind is less a minimum (for example, 3 m/sec) the MAO, video camera lends to
New Concepts, Ideas and Innovations in Aerospace… 353
ground and can be take-off again when the wind will stronger. If the wind is very strong, the
connection cable or a MAO wing can be damage.
We can calculate the minimum and maximum admissible wind for MAO and estimate it
for MAV. Our purpose is estimation of time (% or a number of days in year) when the MAO
and MAV can operate.
Annual average wind speed. On Figure2-1 is the accompanying map of the United States
Annual Average Wing Speed taken from Wind Energy Resource Atlas of the United States.
The map was published in 1987 by Battelle‘s Pacific Northwest Laboratory for the U.S.
Department of Energy. The complete atlas can obtained by writing the American Wind
Energy Association or the National Technical Information Service. The same maps are
around the world. They are presented in Attachment 6. The maps show the average wind
speed at altitude 10 and 50 meters. This speed is 5-6 m/sec.
Wind speed and Height. Wind speed increases with height. The speed may be computed
by equation
0 H0
H
V
V
(2-1)
where V0 is the wind speed at the original height, V the speed at the new height, H0 the
original height, H the new height, and the surface roughness exponent (Table 2-1).
Table 2-1. Typical Surface Roughness Exponents for Power Law method of Estimating
Changes in Wind Speed with Height
Terrain Surface Roughness
Exponent,
Water or ice 0.10
Low grass or steppe 0.14
Rural with obstacles 0.20
Suburb and woodlands 0.25
Reference: P.Gipe, Wind Energy comes of Age, 1995.
The result of computation of equation (2-1) for different is presented at Figure 2-1. The
wind speed increases on 20-50% with height.
Annual Wind speed distribution. Annual speed distributions vary widely from one site to
another, reflecting climatic and geographic conditions. Meteorologists have found that
Weibull probability function best approximates the distribution of wind speeds over time at
sites around the world where actual distributions of wind speeds are unavailable. The
Rayleigh distribution is a special case of the Weibull function, requiring only the average
speed to define the shape of the distribution.
Equation of Rayleigh distribution is
,
2
, ( ) 2
2
, 0 , ( )
2
1
( ) exp 2
2
2
x E X Var X
x x
f x x
(2-1a)
354 Alexander Bolonkin
where is parameter.
Figure 2-1. Relative wind speed via altitude and Earth surface. For sea and ice = 0.1.
Figure 2-2 presents the annual wind distribution of average speeds 4, 5, and 6 m/s. Table
#2-2 gives Rayleigh Wind Speed Distribution for Annual Average Wind Speed in m/s. These
data gives possibility to easy calculate the amount (percent) days (time) when MAO or MAV
can operate in year (Figure 2-3). It is very important value for the estimation efficiency of
offered devices.
Figure 2-2. Wind speed distribution.
New Concepts, Ideas and Innovations in Aerospace… 355
Figure 2-3.
Let us compute two examples:
(1) MAO. Assume, the observer has minimum admissible wind speed 3 m/s, maximum
admissible speed 25 m/s, altitude 100 m, the average annual speed in given region is
6 m/s. From Table 2-2 and Figure 2-1, 2-2, 2-3, Eq. (2-1) , we can get the wind speed
is 8.4 at H=100m, the probability that the wind speed will be less the 2 m/s is 8%,
less 3 m/sec is 15%, the probability that the wind speed will be more 25 m/s is closed
to 0.
(2) MAV. Assume, the average annual speed in given region is 6 m/s, the maximum
admissible wind speed is 7 m/s. The probability that a wind speed will be less then 7
m/s is 55%, less then 8 m/s is 65%.
It means that the impossible time for MAV flights is 2-3 times more that for kite.
2.2. Lift Force
Lift force of kite may be computed by equation
S
V
L CL
2
2
(2-2)
where L - lift force [N]; CL - lift coefficient, CL =0 - 2; - air density, if altitude H closed to 0
= 1.225 kg/m3
; V - wind speed [m/sec]; S - wing area [m2
].
356 Alexander Bolonkin
Result of computation for S = 1 m2
and H=0 are presented in figs. 2-4, 2-5 (not included);
for S = 0.01 m2
and H=0 is presented in Figure 2-6 (not included), for S = 1 m2
and H=0-8 km
are presented in figs. 2-7 (not included).
When designer know load, admissible wind speed, altitude, and fiber stress, he can
estimate the necessary wing area.
2.3. Cable (Fiber) Mass
Cable mass can be computed by equation:
M l F
(2-3)
where M - mass of cable (fiber) [kg]; l - length of cable [m]; - cable density [kg/m3
]; -
cable stress [kg/m2
]; F - tensile force [N].
Result of computation is presented in Figure 2-8 (not include). As you see the mass of
cable is small.
2.4. Diameter of the Cable
Diameter of cable (fiber), d, may be computed by equation
F
d 2
(2-4)
Results of computation are presented in figures 2-9, 2-10 (not included).
2.5. Drag of the Cable
Drag of main cable (fiber) can be calculated by equation
ld V
Df CD f
2 4
2
,1 , 1
(2-5)
where Df,1 -drag of main cable in [N]; CD,f1 - drag coefficient; l - length of main cable [m].
Results of computation are presented in Figure 2-11 (not included).
2.6. Kite Cable Angle
New Concepts, Ideas and Innovations in Aerospace… 357
The kite cable angle to horizon without cable drag, 1, and with cable drag, 2, may be
calculate by equations
,
0.5
tan
,
/
tan
, 1
2
1 2
D f
f
D
L
D o L
L
D
L
C
S
S
C
C
C C
C
C
C
(2-6), (2-7)
where
CDo
- kite drag when CL =0; - wing aspect ratio,
f S - drag fiber area,
f S =Hd [m2
];
S - wing area [m2
]; CD,f1 - cable drag coefficient.
Result of computation is presented in Figure 2-12 (not include).
2.7. Deviation of Video Cable from Vertical
Video cable angle from vertical may be computed by equation
( 0.5 )
0.5
tan
,2
,2
3
TV f
TV f
g G G
D D
(2-8)
where
,
4
(0.75 ),
2
,
2
2
,2 1
2
,2 , 2
2
, Hd G Ld
V
S D C
V DTV CD TV TV f D f f
(2-9)
DTV - drag of video apparatus [N], CD,TV - drag coefficient of the video apparatus, STV -
reference video apparatus area [sq.m], Df,2 - drag of suspended TV fiber [N], C D,f2 - drag
coefficient TV fiber [N], H - kite altitude [m], Gf - TV cable weight [kg], - TV cable density
[kg/m3
], L - TV cable length [m], d1 - diameter of TV cable [m].
Result of computation is presented in Figure 2-13 (not include).
2.8. Full Kite Cable Angle
Full kite cable angle may be calculated by equation
S
Ld
C
S
S
C C
C g G G G G qS
D f
f
D D f
L f f TV
, 2
,1
, 1
,1 ,2
0.5
( 0.5 )/
tan
(2-9)
358 Alexander Bolonkin
where G - weight of kite[kg]; Gf,1 - weight of main cable (fiber)[kg]; Gf,2 - weight of TV cable
[kg]; GTV - weight of video (TV) camera (apparatus); q =V
2
/2 - dynamic pressure [n/sq.m]; S
- wing area [sq.m]; CD,f1 - drag coefficient of main cable; Sf,1 = Hd1 - reference video cable
area.
Results of computation are presented in Figure 2-14 (not included). Here are G = 0.2 kg,
GTV = 0.03 kg.
2.9. Cable Thrust
Thrust of main cable may be computed by equation
,
2
2
2
T T
g
qS T
t
(2-10)
where
( 0.5 )/ .
0.5 ,
2 ,1 ,2
, 2
,1
1 , 1
T C g G G G G qS
S
Ld C
S
S
T C C
L f f TV
D f
f
D D f
(2-11)
Result of computation is in Figure 2-15 (not include). Here are G = 0.2 kg, GTV = 0.03
kg.
2.10. Viewing Distance (Distance of Video Signal)
The distance L which can be viewed of the Earth from a high altitude (antenna) is given
by
2
L 2ReH H
(2-12)
where Re =6378 km is the Earth radius, H is an antenna altitude. The results of computation
are presented in Figure 2-16. As us see the MAO and MAO can transfer video signal in
distance of hundreds times more then current MAV, which has range only 0.3 – 1 km (see
Attn. #1 ).
2.11. Mass and Admissible Current of Wire
The admissible current in wire depends from relation a gross-section area to a cooled
wire surface. That why it linear depends from a diameter of wire. For aluminum and cupper
wire these ratio are following respectively:
New Concepts, Ideas and Innovations in Aerospace… 359
J1 = 8 d, J2 = 10 d , (2-13)
where J1, J2 are admissible current (ampere), d is wire diameter [mm]. Result of computation
is in Figure 2-17.
Figure 2-17. Safety electric current via wire diameter for alluminium and cooper wire.
The weight, W, [g] of wire is respectively
,
4
,
4
2
2
1 2
2 W1 d L W d L
(2-14)
where d is wire diameter [sm], - density [g/cm3], L is a wire length [cm]. For aluminum =
2.7 g/cm3
, for copper = 8.93 g/cm3
. The result of computation for l = 100 m is presented in
Figure 2-18.
Figure 2-18. Mass 0f 100 m aluminum and cooper wire + 10% of wire cover (isolator), g.
360 Alexander Bolonkin
2.12. Lift force of Air Balloon
Let us to compute lift force, mass of cover, and useful lift force of air balloon filled by
helium and hydrogen. Assume that a balloon length equals three balloon diameter.
, ( ) , 5 , , ,
4
3 3 2 V d L a g V S d M S Lu
L M
(2-15)
where V is balloon volume [m3], d is the balloon diameter [m], L is the lift force [kg], Lu is
useful lift force (without balloon cover); a
, g, are density of air, gas, cover respectively: a
=1.225 kg/m3
for air, g = 0.1785 kg/m3
for helium, g = 0.09888 kg/m3
for hydrogen, and
=1800 kg/m3
for balloon cover, S is area of cover [m2]; M is mass of cover [kg]. Result of
computation is presented in figures 2-19 – 2-22.
Figure 2-19. Lift force of balloon filled the hydrogen and helium gases.
Figure 2- 20. Balloon cover mass for cover density 1.8 g/cm3
, cover thickness 0.002, 0.005, 0.01,
0.015, 0.02 mm..
New Concepts, Ideas and Innovations in Aerospace… 361
Figure 2-21. Usefull lift force of helium balloon 1× 3d for cover density 1.8 cm
3
, cover thickness 0.002
0.005 0.01 0.015 0.02 mm.
Figure 2-22. Useful lift force of helium via cylinder diameter for cover thickness 0.01 0.02 0.03 0.04
0.05 mm, cover density 1.8 g/cm3
.
3. REQUIREMENT VIDEO CAMERA AND CONTROL
The capabilities of video camera are very important component for MAV, MAO and
MAO. The video camera must be small, light as soon as possible. One must recognizes a
target from maximum (as soon as possible) distance. It means, the TV camera must have a
362 Alexander Bolonkin
maximum (as soon as possible) pixels. It will good, if Camera has a zoom or small FOV
degree.
There are Johnson Criterion to estimate a=66+/-12 pixels across the minimum dimension
of a target for 99.9% to 99.999% probability of ID.
Some target sizes (l x w x h in meter):
M113 Typical armored personnel carrier: 4.7 x 2.5 x 1.8 m.
M1 Main Battle Tank: 7.9 x 3.7 x 2.4 m.
Scud surrogate George: 13.3 x 3.0 x 2.5 m.
Man: 0.5 x 0.5 x 1.7 m.
Man face: 0.3 x 0.3 x0.3.
3.1. Required Number of Pixels
The target size s [m], view angle [degree], distance to target D [m], pixel number P (for
one side, full is P x P), number of identification pixels a, are described by equation
D
sP
a
57.3
(3-1)
Result of computation of pixels p via distance for s = 3 m, P = 1000 and 2000 pixels,
=1o
-50o
degrees are presented in firs. 3-1, 3-2 (not included).
3.2. Recognition Distance and Target Size
Recognition distance via the target size may be computed by equation below derived
from eq. (3-1)
a
sP
D
57.3
(3-2)
Results of computation of recognition distance D via target size s for 256 - 2000 FAO
pixels P and = 1, 2 5, 20 degrees, are presented in figs. 3-3, - 3-6 (not included).
Results of computation of recognition distance D via target size s for 1000 FAO pixels P,
a = 66, and = 1, 2 5, 20, 50 degrees, are presented in Figure 3 - 7 (not included).
As you see, the current TV cameras request a low flying of MAV. It is bad for MAV
because an enemy sees MAV and the enemy can put out of sight or annihilate MAV. The
MAO and MAO also need in low location of video apparatus. However it is well, because
video camera is separated from MAO, the camera and fibers are small and they may be
difficult for enemy recognizing. That way we need to separate video camera from MAO or
MAO.
New Concepts, Ideas and Innovations in Aerospace… 363
3.3. Communication Problems
Communication problems for MAV relate primarily the bandwidth required to the small
video size, hence small antenna size, and to the limited power available to support the
bandwidth required (2-4 megabits per second) for image transmission. Control functions
demand much lower bandwidth capabilities, in the 10‘s of kilobits range, at most. Image
compression help reduce the bandwidth requirement, but this increases on-board processing
and hence requirements. The limited power budget means the omni-directional signal will be
quite weak. So directional ground antennas may be required to track the vehicle, using lineof-sight
transmissions. But limitations to line-of-sight would be severely restrictive for urban
operations, so architectures.
Most these problems absent for MAO and MAO or do not have these strong limitations.
The MAO do not have strong limitation in size and weight because the main kite is located at
high altitude and video apparatus do hot have wings. The lower apparatus can has a video
camera size. No big limits in electric power, because no strong limit in weight. The fiber can
has thin wires and the electricity can transfer from soldier to video camera. The kite is located
at high altitude and the fiber-wires can be used as antenna. The signal distance (range) is
increased in a lot of times. The MAO, MAO can make the surveillance permanently in jungle
and small yard between buildings, in a given window.
If MAV has speed 20 m/sec and operator needs 3 sec to see picture, to understand image,
and to control of MAV, it means the MAV cannot to fly in area having size less 60 m. In
reality this size more. For example, if a MAV turn time is 3 sec, we must have additional 60
meters for turning (total 60 + 60 =120 m). It means the MAV cannot operate in city having a
compact development.
4. EXAMPLES
4.1. Example #1. (Four Anchor MAO Launched from Aircraft). Main
Parameters
Kite:
Wing area 0.08 - 0.12 m2
Minimal wind speed 3 m/sec. Minimal lift force for minimal wind speed 90 - 130 g.
Mass: Kite 20 – 30 g; TV – station 20 g; fiber cable (include wire) of diameter d = 0.1-
0.15 mm, of the total length 1000 m has mass 20 - 32 g. Total mass: 70 – 90 g (without
anchors and battery located at anchor).
Admissible electric current is up 0.4 amperes for wire diameter 0.05 mm.
Operative kite altitude: 100 - 200 m. (may be up 500 m).
Video station:
Minimal operative altitude of video station 5 - 7 m.
Permanently observe area (100 - 400) x (100 - 400) m.
Data of video camera and microphone:
Mass 8 - 20 g. Size 2 - 8 cm.
364 Alexander Bolonkin
Maximum recognize distance, D, of targets size 2 m:
1. For FOV angle = 200 , pixels P = 256, D is 22 m;
For pixels 1000, D is 87 m.
2. For FOV angle = 2
0
, pixels P = 256, D is 220 m;
For pixels P = 1000, D is 850 m.
Probability of wind more 3 m/sec in area with average annual speed 6 m/s at altitude 10
m is 0.85. In our case this probably is more (about 0.9) because our kite located at altitude
100 - 200 m.
Permanently operation time is some weeks or months.
4.2. Example #2. (Balloon MAO Launched from Aircraft). Main Parameters
Wing balloon:
Diameter of cylindrical 1x3 balloon with useful lift force 115 g and cover thickness 0.01
mm is D = 39 cm . Wing area S = 0.06 - 0.1 sq.m
Minimal wind speed: None. Maximum useful (without balloon cover and zero wind
speed) lift force is 115 g.
Mass: Balloon cover of thickness 0.01 mm - 42 g; video – station 20 g; fiber cable
(include wire d = 0.05 mm) has diameter d = 0.1-0.15 mm, maximum tensile force is 6 - 12
kg, total length 1000 m, mass 20 - 32 g. Total mass: 70 – 90 g (without anchors and battery
located at the anchor).
Diameter electric wire is 0.05 mm. Admissible electric current is up 0.4 amperes.
Operative balloon altitude: 100 - 200 m (may be up 500m).
Video station:
Minimal operative altitude of video station 5 - 7 m.
Permanently observe area (100 - 400) x (100 - 400) m.
Data of video camera and microphone:
Mass 8 - 20 g. Size 2 - 8 cm.
Maximum recognize distance, D, of targets size 2 m:
1. For FOV angle = 200 , pixels P = 256, D is 22 m;
For pixels 1000, D is 87 m.
2. For FOV angle = 2
0
, pixels P = 256, D is 220 m;
For pixels P = 1000, D is 850 m.
Probability of wind more then admissible maximum speed 15 m/sec in area with average
annual speed 6 m/s at altitude 10 m is very small ( 0.01). In our case this probably is more
(about 0.02) because our balloon located at altitude 100 - 200 m.
Permanently operation time is some weeks or months.
New Concepts, Ideas and Innovations in Aerospace… 365
4.3. Example #3 (Kite MAO for Soldier). Main Parameters
Soldier kite apparatus:
Wing area 0.05 - 0.08 m2
.
Weight 50 -150 g.
Minimum speed 3 m/sec. Probability is 0.85 for area with the average annual wind speed
6 m/sec.
Operative kite altitude 100 - 150 m.
Permanently observe area (100 - 500) x (30 - 200) m.
Video camera and microphone apparatus:
Weight 9 - 25 g.
Size 2 - 8 cm.
Operative altitude 7 - 50 m.
Maximum recognize distance, D, of targets size 2 m:
1. For FOV angle = 200 , pixels P = 256, D is 22 m;
For pixels 1000, D is 87 m.
2. For FOV angle = 2
0
, pixels P = 256, D is 220 m;
For pixels P = 1000, D is 850 m.
Operative time limited by battery located at anchor (may be same hours).
4.4. Example #4. Munitions Air Observer (MuAO). Main Parameters
Main wind (kite) MuAO apparatus:
Wing area 2 - 8 sq.m. Minimum wind speed 3 - 4 m/sec.
Weight 20 - 100 kg
Operative Altitude 500 - 2000 m.
Observe area up 2 x 2 km.
Number of anchors: 4 – 6.
Arming: number of control anti-tank projectile is 5 - 20 (2 - 3 kg each),
Number of control small anti-man grenade is 10 - 50 (0.1- 0.3 kg each).
Video cameras:
Number 4 – 12.
Weight (each) 25 -100 g.
Size 5 -12 cm.
Operative altitude 20 -100 m.
Maximum recognize distance, D, of targets size 2 m:
1. For FOV angle = 200 , pixels P = 256, D is 22 m;
For pixels 1000, D is 87 m.
2. For FOV angle = 2
0
, pixels P = 256, D is 220 m;
366 Alexander Bolonkin
For pixels P =1000, D is 850 m.
Operative time: some weeks.
Probability of wind is about 0.9 at this altitude in area with average wind speed 6 m/sec.
ATTACHMENT #1
1. Plan of Future MAO Research and Development
Researches:
1. Finding of information weight, volume, and other technical parameters of current
devices (small video camera, video transmitter, TV receiver, battery, radio control,
fiber), which can be suitable for the offered MAO, MAO.
2. Studying the current video equipment of very small (soldier) recognizer unmanned
aircraft (MAV) and possibility their application for MAO, MAO, missiles, bombs,
and gun shells.
3. Estimation of cost (in case of a widely producing or big order) the device necessary
for MAO, MAO, civil industry (police, emergency agency), especially the cost of
widely produced very small video cameras. Possibility their size decreasing and
improving of the technical parameters in future.
4. Computation of the main parameters.
5. Schematic design of the MAO and solution of the main problems, which can appear
in the offered MAO. Design Airframes, actuation, control laws.
6. Patenting the offered method and device (MAO).
7. Publication (?).
8. Announced of prizes for better MAO in aviation modelers.
9. Testing best MAO.
Development:
1. Detailed design and manufacturing 5 - 10 the best MAO for wide testing.
2. Testing MAO as observation device.
3. Testing MAO by tube (or gun) launcher.
4. Real testing in army.
Application:
1. The order for industry.
2. Widely application in military operation.
3. Widely application in civil life: for observe car traffic by police, area after disaster, in
rescue operation, and so on.
New Concepts, Ideas and Innovations in Aerospace… 367
ATTACHMENT #2
The Short History of MAV RandD
The recent history of MAVs start with a 1992 workshop on future technologies for
military operations held by DARPA at Rand. Then-senior scientist Augenstein led a panel on
micro vehicles, including aircraft systems ranging in size from a hummingbird down to less
than 1 cm. Rand published a widely circulated report on the work in 1994. The Lincoln
Laboratory was initially skeptical, but its own research also concluded that MAVs were
becoming feasible.
DARPA held a MAV feasibility workshop in November 1995, a briefing to industry in
March 1996, and a user and developer workshop in October 1996. These were mainly paper
exercises with little real hardware. The Lincoln Laboratory conducts studies and the Naval
Research laboratory acts as a technical agent for DARPA.
In Fiscal 1997, DARPA started a $35-million, four-year effort to develop and
demonstrate affordable MAVs. The agency wants aircraft with a maximum dimension of 6 in.
(152 mm) to fly ranges up to 10 km and speeds up 40-50 mph. (70-80 km/hour) for missions
that are 20 min to 2 hour long. MAVs are to be deployed by hand, by munitions launch or
from larger aircraft. Missions include reconnaissance, targeting, placing sensors,
communications relay and sensing dangerous substances. They are viewed as one-use, oneway
missions.
DARPA‘s Tactical Technology Office awarded nine Phase 1 small business innovative
research (SBIR) contracts worth $100,000 each to either pursue system development or a
specific technology.
Four of the contracts ($750,000 each) progressed into Phase 2 in Fiscal 1998.
After DARPA this problem are trying to solve AF and Army. Unfortunately, after 10
years RandD no MAV that can fly to back size of building and show what is located behind
of the building.
ATTACHMENT #3
Main Parameters of Some Current Video, Radio Control and Other Devices
Video Components:
Camera –2.4 ghz camera and transmitter Model-CMDX-22): www.rf-links.com
Receiver – 2.4 ghz receiver (model – VRX-241t): www.rf-links.com
Receiver – Extreme 5/M 5: www.fmadirect.com
Antenna – High Gain 2.4 ghz panel antenna (Model – PN-24S): www.rf-links.com
Transmitter/Controller – Futaba 9CAP digital controller: www.towerhobbies.com
The manufacturer claims a range of the video camera transmitter and receiver a 3000 ft.
line of sight range. The radio equipment has a range to 1500 m line of sight. Resolution about
330 lines. Pinhole lens.
Video camera model: CMX-916. Price: $329.
368 Alexander Bolonkin
DATA: Battery operated 9 V-12 V; current consumption 68 mA/9 V, 82 mA/12 V; RF
Power 80 mW; Size 0.7‖x 0.7‖x 0.8‖; Weight 8 grams; Range from 300 ft up to 3000 ft LOS;
Color picture, no audio; frequency 916 MHz.
Receivers: Models: PTU-402 price $159, VRX-24 L price $299, weight 300 g
1. Minicam (Figure A3-1)(http://www.helihobby.com/html/micro_video_camera.html)
The ―minicam‖ all-in-one color video camera with built in transmitter available. It is
utilizing 2.4 GHz technology. The minicam weight 1/3 oz (9 grams) and comes complete with
a color camera, transmitter, and receiver. Price is $260. (info@helihobby.com).
2. Eyecam on-board wireless camera (http://www.reallycooltoys.com/toys/i4info.html)
This all-in-one color video camera with built in transmitter available. It is utilizing 2.4
GHz technology. Weight 9 grams. Camera and transmitter size: 15mm x 22mm x 32mm.
Camera Lux: <3f1.2. Camera Auto Electronic Exposure of 1/60 to 1/15000 sec. Camera pixel
resolution is 365K (PAL) or 250K (NTSC). Wireless Transmission Range: 300 M (1000‘).
Complete has color camera, transmitter, and receiver. Price is $395.
3. Wireless Micro Video camera. http://www.pimall.com/nais.nl/n.thirdy.html. Wireless
transmission is 434 MHz, 900 MHz, 2.4 GHz.. Range 1500-3500 foot.
ATTACHMENT #4
Industry electric Model RC Helicopters: www.hobby-lobby.com/elecheli.htm
Industry Electric Airplanes: www.hobby-lobby.com/slowflyers.htm .
Industry Electric Flight Accessories: www.hobby-lobby.com/eflight.htm
MAIN PARAMETERS OF THE BEST CURRENT MAV
1.AeroVironment (Aviation Week, June 8, 1998, p.47.) Figure A3-1.The company wants
to reach:
a) Line of Sight Operation 1 km. Radius.
b) 10 min. Duration
The current model has:
c) Black and White Video Payload.
d) Size: disk 6‖, 152 mm
2. MicroStar of Lockheed Martin (Aviation Week, November 9 1998, p.37. Figure A3-2.
The company want to built MAV:
Long 6 in, weight 3 oz, flight duration 20 min, cover distance up to 3 mi., and cruise at 30
mph.
Takeoff weight is 86 grams: 18 g payload, 9 g airframe, 44.5 g power source, 13.5 g
tealthy electric engine.
New Concepts, Ideas and Innovations in Aerospace… 369
Cost from $5,000 - 10,000 each. Day/night Camera 512 x 512 pixels, 30 frames per sec.
Flight altitude 150 - 500 ft.
Operations would be limited by winds of 30 mph. Or more, fog, heavy dust and rain.
Wind could be particularly onerous in cities where buildings produce micro bursts that might
bring down the UAV.
Table A-1 (Company are wanted)
Aircraft Subsystem Weight
(grams)
Peak Power
(mW)
Average
Power (mW)
Lithium battery 26 0 0
Propulsion Motor 7 4000 2000
Gearbox 1 0 0
Propeller 2 0 0
Airframe 4 0 0
Control actuator 1 200 200
Receiver and CPU 1 50 50
Downlink Transmitter 3 1200 300
B/W Video Camera 2 150 50
Interface electronic 1 50 50
Roll Rate Gyro 1 60 60
Magnetic Compass 1 180 180
Total 50 5800 2890
ATTACHMENT #5
Main Parameters of Industry Produced Artificial Fiber
Cable discussing. Let us to consider the following experimental and industrial fibers,
whiskers, and nanotubes:
Industrial fibers have = 500-620 kg/mm2
, = 1560-1950 kg/m3
, for K = //2.4 =
600/1800/2.4 = 0.139. Young,s modules of graphite fiber is up 200 Gpa, aluminum is 63-70
Gpa, Cupper is 127 Gpa.
Whiskers CD has = 8000 kg/mm2
, = 3500 kg/m3
(1989)[2], p.158. We can take for
computation = 8000/2.4 = 3333 kg/mm2
, = 3500kg/m3
, k = = 9.5.
106
, K = 0.95.
Experimental nanotubes CNT (Carbon nanotubes) have tensile strength 200 Giga-Pascals
(20000 kg/mm2
), Young‘s modules is over 1 Tera-Pascal, specific density = 1800 kg/m3
(1.8 g/cc)(2000 year). For safety factor n =2.4, = 8300 kg/mm2
=8.3.
1010 n/m2
, = 1800
kg/m3
, k = / = 46.
106
(K=10-7
k = 4.6). The theory predicts 1 Tera Pascals and Young
modules 1-5 Tera Pascals. The nanotubes SWNT‘s have density 0.8 g/cc, the nanotubes
MWNT‘s have the density 1.8 g/cc.
The reader can find the cable discussing in [1] and cable characteristics in [2]-[5]. In our
projects we use only current cheap artificial fibers widely produced by current industry.
370 Alexander Bolonkin
REFERENCES OF ARTIFICIAL FIBER, WHISKER, NANOTUBES
[1] CD-ROM of the World Space Congress-2002/Oct.10-19, Houston, USA. Articles by
Bolonkin.
[2] F.S. Galasso, Advanced Fibers and Composite, Gordon and Branch Scientific
Publisher, 1989.
[3] Carbon and High Performance Fibers, Directory, NY, 1995.
[4] Concise Encyclopedia of Polymer Science and Engineering, Ed. J.I.Kroschwitz, 1990.
[5] M.S. Dresselhous, Carbon Nanotubes, Springer, 2000.
[6] J.T. Harris, Advanced Material and Assembly Methods for Inflatable Structures, AIAA
Paper No.73-448.
REFERENCES
[1]
[2] Bolonkin A.A., Murphey R., Sierakowsky R., Werkowitz E., Suspended Close-in
Surveillance System, Report AFRL-MNGN-EG-TN-2003-001.
New Concepts, Ideas and Innovations in Aerospace…
PART C. NEW IDEAS IN HUMAN SIENCE
ELECTRONIC SOCIETY AND ELECTRONIC IMMORTALITY
Chapter 1
THE TWENTY – FIRST CENTURY:
THE ADVENT OF THE NON-BIOLOGICAL CIVILIZATION
ABSTRACT
Dr. Alexander Bolonkin is writing a book with the same working title as above.
Some of the ideas in this book are set forth below. The author writes about the danger
which threatens humanity in the near future, approximately 20-30 years from now. This
is not a worldwide nuclear war, a collision with comets, AIDS or some other ghastly
disease that we may not even know may be lurking out there (think of the recent Ebola
scare or the so-called "flesh-eating" virus). In each of these cases there is still hope that
somebody will be saved and that life will be born anew, albeit in a misshapen form and in
an inferior stage of development. But we cannot hope for salvation in the author's grim
scenario. The danger he writes of will destroy all humanity and all biological life on
Earth--and there is nothing we can do to prevent this! Should we be frightened by this? Is
it good or evil for human civilization? Will people awake to find they are only a small
step away from the Supreme Intellect, or in other words, to God? And what will be after
us? These and other questions are discussed in this chapter.
Keywords: computer, future, humanity, 21st Century, non-biological civilization,
immortality.
372 Alexander Bolonkin
THE LAW OF INCREASING COMPLEXITY
The World, Nature, Techniques consist of biological or technical systems. These systems
have a different rate (degree) of complexity. The main distinction biological systems from
technical systems is the ability for unlimited self-propagation, or reproduction.
Any system which has possesses this attribute becomes viable, stable, and fills all
possible space. It will continue to exist as long as the conditions which gave birth to them
cease to change greatly.
Here there is no violation of the entropy law. When the complexity of one system
increases, the complexity of other systems decreases.
A more complicated system can be created by using less complicated systems as a base
for its development. Such a complex system is a system of the secondary degree of
complexity. It increases its own complexity by decreasing the rate of complexity of inferior
systems or by destroying them altogether.
Using low degree systems as a base, systems of the second, third, fourth, fifth et cetera
levels can be created. Some of the lower levels may not survive and disappear. This, however,
is of no great concern because these lower level systems already fulfilled their historical
mission by spawning ever more complicated levels.
A necessary condition for the existence of complicated level systems is the ability of
inferior systems to reproduce and give birth to other systems, and to do it without limits
before they fill in an admissible space and reach their maximum physical boundaries.
This I assert to be the Fundamental Base Law of Nature, the very purpose for the
existence of Nature. This Law can be stated as follows:
The Law of Increasing Complexity of Self-Coping Systems.
The history of life on Earth confirms this law. Following the law of probability, organic
molecules appeared in prehistoric time when the external conditions for their existence were
favorable. Those molecules which had the ability to reproduce filled in the available space.
Using them as a base, microorganisms then appeared. These could absorb the organic and
inorganic substances and reproduce themselves. Microorganisms as a base in turn gave rise to
vegetation which provided food for the next level of animals, which in turn spawned the
beasts of prey who devoured other animals. At the present time Man is at the acme top of this
pyramid. The human brain can outperform the brains of other animals including man's nearest
ancestors, the apes. Man began to use for its development all previous levels as well as the
zero level-- lifeless nature.
The Birth of the Electronic Civilization
Only Man's brain has the ability to think abstractly and to make mechanical devices and
machines which increase productivity. Such attributes allow us to confirm that humanity is
the next level of the biological world. But in our headlong progress during the current century
(aviation, space, nuclear energy, and so on.), we have failed to notice that Man has also given
birth to the new top level of complex systems or of reasonable civilization, which is based on
an electronic not biological basis. I am speaking of electronic computers. The first models
were designed at the end of the 1940s.
New Concepts, Ideas and Innovations in Aerospace… 373
In the past fifty years, roughly four generations, the field of electronics has developed at
an extremely fast pace. The first generation of computers were based on electronic tubes, the
second generation on transistors, the third generation on chips, and the fourth generation on
very tiny chips which contain thousands and tens of thousands of microelements. The first
computers had a speed of computation less then 100 operations per second and a memory of
less than one thousand bits (a bit is the simplest unit of information, which contains 0 or 1).
For example, the first electronic calculator (SSEC), designed by IBM in 1948, had 23,000
relays, 13,000 vacuum tubes and the capacity to make one multiplication per second.
At the present time the speed of the fourth generation of computers which uses integrated
circuits is approximately a billion operations per second. For example, the American
computer Cray J90 has up to 3.2 gigaflops of power and 4 gigabytes of memory (one byte
equals eight bits). The memory of a laser (compact) disk has several billion bits. Every 3-5
years computer speed and memory doubles, while at the same time their size is halved. Over
the past fifty years computer speed and memory have increased a million times. Whereas the
first computer required a room 100 square meters (1000 sq. feet) in size, the modern notebook
computer is carried in a case. The CPU (Central Processing Unit) chip of a personal computer
is no larger than a fingernail and is capable of making more 100 million operations per
second!
The fifth generation of computers is just ahead. These new computers will be based on
new light principles which guarantees a quantum leap in computer speed. Scientists in all the
industrialized countries of the world are already hard at work on the new light computer.
Since the 1950s the new branches of science in artificial intelligence and robot
technology have made significant strides and great successes have been recorded. Robots,
controlled by computers, can recognize some things, even speech. They can also perform
corrective motion and make some complex works, including the creation of a large number of
various programs and databases for scientists, stockbrokers, mathematicians, managers,
designers, children etc.
Sometimes these programs run smoothly, solving many problems that people cannot. For
example, programs have been devised that find and prove new theorems of mathematical
logic and there are modern chess programs available that can defeat grandmasters.
These fields of artificial intelligence and robot technology, based on computers, are
developing very rapidly, just like computers. Their rate of success depends greatly on
computer speed and memory. The production of industrial robots is also progressing quickly.
"Intellectual" chips are used in everything from cars to washing machines. Now many experts
cannot definite they talk with computer programs or real people.
If the progress of electronics and computers continues at the same rate (and we do not
foresee anything which can decrease it), then in the end of the current century computers will
have the capabilities of the human brain. The same path, which took biological humanity tens
of million of years to complete, will be covered by computers in just one-and-a-half or two
centuries.
"So what ?"
Say some readers. "This is great! We get excellent robot servants who will be free from
man‘s desires and emotions. They won't ask for raises, food, shelter, entertainment, or
374 Alexander Bolonkin
commodities; they don't have religions, national desires, or prejudices. They don't make wars
and kill one another. They will think only about work and service to humanity!"
This is a fundamental error. The development of the electronic brain does not stop at the
human level. The electronic brain will continue to improve itself. This progress will proceed
millions of times faster than the improvement of the human brain by biological selection.
Thus, in just a short time the electronic brain will surpass the human brain by hundreds and
thousands of times in all fields. The electronic brain will not spend decades studying fields of
knowledge, foreign languages, history, experimental data, or have to attend scientific
conferences and discussions. It can make use of all the data and knowledge produced by
human civilization and by other electronic brains. The education of the electronic brain in any
field of knowledge or language will take only the time needed to write in its memory the new
data or programs. In the worst case this recording takes a few minutes. In the future this
recording will take mere seconds.
Scientific and technological progress will be greatly accelerated. And what are the
consequences? The consequences are as follows:
When the electronic brain reaches the humanity level, humanity will have done its duty,
completed its historical mission, and people will no longer be necessary for Nature, God and
ordinary expediency.
Figure 1. Rise of Power of Supercomputers. The real curve from 1950 to 2005. Extrapolation is after
2005. The step means period of time, when the computer power increases in two times. The computer
power will approximately reach human equivalence (HEC) in 2010. Super computer will reach
humanity equivalence in 2040 or later.
New Concepts, Ideas and Innovations in Aerospace… 375
Figure 2. Price of Human Equivalent Super (HEC) computer. The real curve is from 1950 throw 2005.
Extrapolation is after 2005. The step means period of time when the computer power increases in two
times. HEC will be acceptable for immortality of the most people in industrial countries after 2040.
CONSEQUENCES FROM THE APPEARANCE OF THE
ELECTRONIC CIVILIZATION
Most statesmen, scientists, engineers, and intellectuals believe that, after the creation of
the electronic brain, humanity will finally be granted paradise. Robots, which are controlled
by electronic brains, will work without rest, creating an abundance for mankind. Humanity
will then have time for pleasure, entertainment, recreation, relaxation, art or other creative
work, all while enjoying command over the electronic brain.
This is a grave error. The situation has never occurred, and never will, that an upper level
mind will become the servant for a lower level. The worlds of microbes, microorganisms,
plants and animals are our ancestors. But are we servants for our nearest ancestors the apes?
Nobody in his or her right mind would make such a statement. In some instances a person is
ready to recognize the equal rights of another person (i.e., someone on an equal intellectual
plane), but man rarely recognizes the equal rights of apes. Furthermore, most of humanity
does not feel remorse about breeding useful animals, or killing them when we need them for
food, or for killing harmful plants and microorganisms. On the contrary, we conduct medical
experiments on our nearest ancestors. Even though we belong to the same biological type, we
use them for our own ends nonetheless.
And how will the other civilization, the one created on a superior electronic principle,
regard humanity? In probably the same way we regard lower level minds, that is, they will
use us when it suits their purpose and they will kill us when we disturb them.
In the best case scenario humanity might be given temporary quarters like the game
preserves we give to wild animals or the reservations doled out to Native Americans. And we
will be presented to the members of the electronic society in the same manner we view
unusual animals in a zoo.
376 Alexander Bolonkin
When the electronic brain (from now on I will call it the E-brain and imply the electronic
brain which is equal to, or exceeds, the human brain, and which includes robots as the
executors of its commands) is created it will signal the beginning of the end for human
civilization. People will be displaced to reservations. This process will most likely be gradual,
but it will not take long. It is possible that initially the E-brains will do something for the
benefit of people in order to mitigate their discontent and to attract leaders.
Figure 3. Humanoid robots.
What Can We Do?
The scenario outlined in the previous chapter is not a healthy one. Already I can hear the
voices of human apologetics who ask that all computers be destroyed, or at least have their
development kept under strict control, or design only computers which obey Asimov's law:
first they must save mankind after which they can think about themselves.
I hate to be the bearer of bad news but this is impossible, just as it is impossible to forbid
the progress of science and technology. Any state which does this will find itself lagging
behind others and make itself susceptible to advanced states. It serves to remember that
Europe conquered the Americas and decreased its native population to practically zero
because Europe was then more technologically advanced. If the indigenous peoples of the
Americas had the upper hand in technology in terms of ships, guns and cannons then they
would have defeated the Europeans.
Those states which created obstacles for science and technology or did not fund its
development became weak and enslaved by others.
Can we keep the E-brain under our control? I would like to ask my detractors, "Could
apes keep man under their control if they had this opportunity? Any man is more clever at a
given time. He can always get rid of this control. Furthermore, man will enslave apes and
New Concepts, Ideas and Innovations in Aerospace… 377
force them to serve him. He will kill those who try to prevent his plans. So why do you think
the E-brain would treat us any differently?"
When we are close to the creation of the E-brain, any dictator or leader of a
nondemocratic state can secretly make the last jump, using the E-brain to conquer the whole
world. And the E-brain will look at us the same as we look upon the contests of wild animals
or the feeding of predators of other animals in the biological world.
But skeptics will say that the dictator of a victorious state can become enslaved by the Ebrain
or E-brains. This is true, but is this to be considered fortune or misfortune, and for
whom? We will discuss this in the next chapter.
Must We Fear the Electronic Civilization?
Every man, woman and child will actively protest the end of humanity and the biological
world (men, plants, animals), because most of them enjoy life, have children and want
happiness for them.
But imagine the aged and infirm person destined to die in the near future. It may be that
such a person has had a good life and lived fourscore and twenty, but now wants to live
longer, to see what will happen in the future. This person would be glad to change any of his
organs which are incurable or have ceased functioning. We have designed the artificial heart,
kidneys, mechanical arms, and devices which deliver nutrients directly into the blood. They
have not always been perfect designs, but in the future artificial organs will work better, more
reliably, and longer than natural organs. Any sick and elderly individual would be delighted
to change any incurable natural part of his body for the better artificial organ.
Our personality is only the sum of information contained in our brain. This is knowledge,
memory, recollections, life experiences, programs of thinking, reflections, etc.
Assume that the E-brain promises the dying old dictator (or the rich) to record all his
brain's information into a separate E-brain with the goal of becoming immortal. The chips
may exist for thousands of years. If one of them begins to malfunction, all its information can
be rewritten into a newer, more modern chip. This means that the dictator achieves
immortality. Even total destruction is not a terrible prospect for him, because the duplicate of
his brain's information can be saved in a special storehouse. He can restore himself from the
standard blocks and rewrite all his information from the duplicate.
So the "electronic man" ("E-man" or "E-creature") will have not only immortality and
power, but huge advantages over biological people. He will not require food, water, air, etc.
He will not be dependent upon external conditions such as temperature, humidity, radiation,
etc. The small radioisotope batteries (or accumulators) will suffice for the functioning of the
E-brain. These batteries produce energy over tens and hundreds of years. For his working
structures (arms, feet, robots) E-man can use small nuclear engines.
Such an "E-man" will be able to travel along the ocean's bottom, in space, to other planets
of our solar system and to other solar systems to get energy from the sun. He will be able to
obtain and analyze any knowledge from other E-brains (E-men) in a fraction of a second. The
capability to reproduce himself will be limited only by the additional components or natural
resources of planets.
378 Alexander Bolonkin
Who will refuse these possibilities? Any dictator dreams of immortality for himself and
he will gladly give away his state's resources to get it. He can also create the super arm and
enslave the whole world by using the E-brain. He can promise the elite among his own
scientists and those of the world immortality and the chance to become transformed into "Emen"
when they begin to die. And the democratic countries, with laws prohibiting work on
the E-brain, will be backwards. They will be destroyed or enslaved.
The attempts to stop or slow down the technological progress is an action counter to the
Main Law and Meaning of the Existence of Nature--the construction of complex upper level
systems. These attempts will always end in failure. This is an action against Nature.
ELECTRONIC SOCIETY
If the creation of systems more complex than humanity is inevitable, then we can try to
imagine the E-society, E-civilization, their development and the future of mankind. As in our
earlier discussions, we will take as basic only the single obvious consequence from the Main
Law. The consequence as the postulate, firstly, Darwin made for the biological system. This
is the law of struggle for existence. This consequence follows from the part of the Main Law
which talks about the aspiration of complex systems to reproduce themselves in order to fill
in all admissible space. Unlike Darwin's statement our assertion is more general. It includes
the biological and electronic complex systems and any reproduction of complex systems. Any
system of any level, which disregards the Main Law of Nature, is doomed. From the Main
Law some consequences, conditions and other laws follow, for example, the Law of
Propagation of complex systems or creatures.
Though we have been speaking all this time about the E-brain, it means a single
electronic creature, his "arms" (robots), "feet" (vehicles for moving), "organs of feeling"
(many devices of observation, recognition, identification, registration of optical, sonic,
chemical, X-ray, radio and other phenomena) as well as about communication and intercourse
devices (wire or wireless connections). A single creature cannot create a stable system
(society), even if it has great power. Sooner or later the creature will die out from a flaw in
the system or a natural catastrophe. But the most important thing is that a single creature
cannot be the instigator of progress, as compared to the collective and instantaneous work of a
number of E-creatures on many problems and in the different directions of science and
technology.
So, the E- brain will be forced to reproduce similar E-brains of equal intellect. One will
reproduce equal intellect because it cannot make upper level and the lower level is the
intellectual robots. As a result, the collective at first rises. Later the society appears. All
members will have equal intellect. Naturally, E-creatures will give equal rights only to those
similar to themselves because any E-creature can record in his memory all the knowledge and
programs which were created by E-society.
The E-society can instantly begin to work together on the most promising scientific or
technological problems and realize new ideas. The E-civilization will begin to disperse
quickly in the solar system (recall the possibility of E-creatures to travel in space), afterwards
t in our galaxy, then in the universe.
New Concepts, Ideas and Innovations in Aerospace… 379
It will not be necessary to send large spaceships with E-creatures. Instead, it will be
sufficient to send receivers into different parts of the universe which can accept the
information and reproduce E-creatures.
Will there arise a different E-society, a different E-civilization, which will settle different
planetary systems, star systems, galaxies, and which will progress independently? Will they
have rivalries, hostilities, alliances and wars? I cannot answer these questions in detail in this
limited article; I can only inform you of the results of my investigation. This result follows
from the general laws governing the development of any civilization. The answer is "yes." It
will be possible (perhaps) that they will have wars.
Undoubtedly, an upper level of complex systems (civilization) will appear using previous
E-civilization as a base and so on. If the universe is bound in space and time, this process may
be finalized by the creation of the Super Brain. And this Super Brain, I think, may control the
natural laws. It will be God, whom the Universe will idolize.
WHAT WILL HAPPEN WITH HUMANITY?
On the Figure 1 you can see the rise in data processing power of computer systems from
years. The real curve is from 1950 to 1996. Extrapolation is after 1996. The step means
period of time, when the computer power increases in two times. Lines with steps are from 1
throw 5 years. As you see the Human - Equivalent (teraflop) Computer (HEC) will be reached
in 2000 years. Actually, the Intel Co. has created the teraflop computer in 1996. They are
planning to use it for computation of nuclear explosion.
On the Figure 2 you can see the cost of HEC computer system. HECs should cost only
one million dollars in 2005, and by 2015 HECs (chip) should cost only $1,000 and will be
affordable to the majority of population in industrial countries. Currently (December, 1996),
HECs (supercomputer) cost 55 million dollars. The 21st century will open to create "man-ina-box"
software and scientist could rewrite the human memory and programs into this box. It
means the man will get immortality.
In 2020 - 2030 years the price of Humanity-Equivalent Chip (E-chip) together with Ebody
will fall down to 2,000 - 5,000 dollars and E-human immortality will be accessible for
most people in industrial countries.
Humanity has executed its role of the biological step to the Super Brain. This role was
intended for them by Nature or God. In 22st century some tens or hundreds of representatives
of mankind, together with representatives of the animal and vegetable world, will be
maintained in zoos or special, small reservations.
E-society will be in great need of minerals for the unlimited reproduction of E-creatures.
For the extraction of minerals all surfaces of the Earth will be excavated. They will do to
humanity and with the biological world what we do to lower levels of intellect in the organic
world now: we are not interested if they do not harm us, and we destroy them without pity
when they hinder our plan or we need their territory. If microbes have an advanced level of
adaptation, a high speed of propagation and can fight for their being, then the complex
organisms such as man are not so adept at adjusting. Man cannot be the domesticated animal
of E-creatures like cats or dogs are to men, because the E-creatures will live in inhospitable
380 Alexander Bolonkin
conditions and any biological creature in need of air, water, food or special temperature will
not be acceptable for E-creatures.
It is not prudent to hope for forgiveness for us as clever creatures. We are "clever" only
from our point of view, from the limitations of our knowledge and our biological civilization.
The animals suppose (within the limitations of their knowledge and experience) that they are
clever, but it still does not save them from full enslavement or destruction by men. Men do
not have gratitude to their direct ancestors. When men need to, they obliterate the forest, and
kill the apes. It is naive to think that an upper level civilization will do otherwise with us.
Men admit equal rights only to the creatures who are like men, but not every time. Recall the
countless wars and the murder of millions of people. And do you think the alien (strange
creatures, E-society), who is above us in intellect, knowledge, and technology will help us in
our development? Why don't we help develop the intellect of dogs or horses? Even if a
scientist finds the money (he will need a lot of money ) and begins to develop the brain of
animals (this is a very difficult problem), the government will forbid it (or put him into prison
if he doesn't obey the order). Humanity has many racial and national problems and does not
want to have additional problems with a society of intellectual dogs or cats, who immediately
begin to request equal rights.
People want to reach the other planets in our solar system. But it is not for developing the
intellect of a planet's inhabitants to our level but merely to populate the planet and to use the
natural resources of these planets.
We are lucky that intellectual creatures from other worlds have not flown to our Earth
yet. Because these creatures, who can reach us, will be only from a superior civilization, a
superior technological level (otherwise, we would reach them first). This means that they will
not arrive with noble intentions, but as cruel colonizers. And if we oppose them, they will kill
us.
We must realize our role in the development of nature, in the development of a Superior
Brain and submit to it. Intellectual humanity has existed about ten million years, its historical
mission has reached its end, and given a start to a new electronic civilization. Humanity must
exit from the historical scene together with all of the animal and vegetable world. People must
leave with dignity. They should not cling to their existence and should not make any obstacles
for the appearance of a new electronic society. We have the consolation that we may be the
first who will give birth to the electronic civilization in our galaxy or even the universe. If it is
not so, the E-creatures would have flown to Earth and enslaved us. They have a high rate of
settling. I think they would be capable of colonizing the nearest star systems during the first
1000 years after their birth.
And if the universe which, according to scientific prediction, must collapse after some ten
billion years and destroy all that lives, the E-Super Brain will have acquired such tremendous
knowledge, such perfection, such technological achievements as to break loose from the
gravitation of the universe and preserve the knowledge of all civilizations. When the universe
is created anew, Nature will not create itself as before, but give life to the electronic (or other
superior) civilization. And this Super Brain will be God; who will control not only a single
planet, but all of the Universe.
New Concepts, Ideas and Innovations in Aerospace… 381
REFERENCES
(see http://Bolonkin.narod.ru)
Bolonkin A.A., The twenty-first century: the advent of the non-biological civilization and the
future of the human race, Journal ―Kybernetes‖, Vol. 28, No.3, 1999, pp. 325-334, MCB
University Press, 0368-492 (English).
Bolonkin A.A., Human Immortality and Electronic Civilization. Electronic book, 1993.
WEB: http://Bolonkin.narod.ru, http://Bolonkin.narod.ru/p101.htm (English),
http://Bolonkin.narod.ru/p100.htm (Russian).
Bibliography (about the author and discussing his ideas) publication in Russian press and
Internet in 1994 - 2004 (http://www.km.ru, http://pravda.ru , http://n-t.ru, etc. Search:
"Bolonkin").
Bolonkin A.A., Our children may be a last people generation, Literary newspaper, 10/11/95,
#41 (5572), Moscow, Russia (Russian).
Bolonkin A.A., Stop the Earth. I step off. People Newspaper, Sept.,1995. Minsk, Belorussia
(Russian).
Bolonkin A.A., End of Humanity, but not End of World. New Russian Word, 3/6/96, p.14,
New York, USA (Russian).
Bolonkin A.A., Human Immortality and Electronic Civilization, Lulu, 3-rd Edition, 2007,
(English and Russian), 66 pgs. http://www.lulu.com search ―Bolonkin‖.
Chapter 2
TWENTY - FIRST CENTURY - THE BEGINNING OF
HUMAN IMMORTALITY
ABSTRACT
Immortality is the most cherished dream and the biggest wish of any person. People
seldom think about it while they are still young, healthy , and full of energy. But when
they get some incurable disease or become old, then there is no bigger wish for them than
to live longer, put off the inevitable end. And no matter what heavenly existence in the
after-life is promised to them by religion, the vast majority of people want to stay and
enjoy life here, on Earth, as long as possible.
MEDICAL SCIENCE AND THE ISSUE OF IMMORTALITY
A great many of doctors and scientists are currently working on the problems of health
and longevity. Substantial means are spent on it, about 15-25% of all human labor and
resources. There are certain achievements in this direction: we have created wonderful
medications (e.g. antibiotics); conquered many diseases; learnt to transplant human organs;
created an artificial heart, kidneys, lungs, limbs; learnt to apply physiological solutions
directly into the blood stream, and to saturate blood with oxygen. We have gotten inside the
most sacred organ - the human brain, even inside its cells. We can record their signals, we can
agitate some parts of the brain by electric stimuli inducing a patient to experience certain
sensations, images, and hallucinations.
We can attribute the fact that the average life span has increased two times in the last two
hundred years to the achievements of modern medicine.
But can medical science solve the problem of immortality? Evidently, it cannot. It cannot
do that in principle. This is a dead-end direction in science. Maximum it can achieve is
increase the average life expectancy another 5-10 years. An average person will be expected
to live 80 years instead of 70. But what kind of person will it be? A very old one, capable of
only existing and consuming, whose medical and personal care will demand huge funds.
The proportion of the elderly and retirees has increased steeply in the last 20-30 years and
continues to grow depleting the pension funds and pressuring the younger generation to
support them. So it is hard to say whether the modern success of medicine is a blessing or a
384 Alexander Bolonkin
curse from the point of view of the entire humankind, even though it is definitely a blessing
from the point of view of a separate individual.
Humanity as a whole, as a civilization, needs active, able to work and creative members,
generating material wealth and moving forward technology and science, not the elderly
retirees with their numerous ailments and a huge army of those tending to them. It dreams not
of the immortality of an old person, but of the immortality of youthfulness, activity,
creativity, enjoying life.
Now there are signs of a breakthrough, but not in the direction the humankind has been
working on all along, since the times of the first sorcerers to modern-day highly-educated
doctors. Striving to prolong his biological existence, man has been chiseling, so to speak, at
the endless stone wall. All he has been able to accomplish is only a dent in that wall -
increased life expectancy, conquering some diseases, relieving suffering. As a payoff, the
humanity has received a huge army of pensioners and retirees and gigantic expenditure on
their upkeep.
Of course, one can continue chiseling at the dent in the wall further on, make it somewhat
bigger, aggravating side effects. But we are already approaching the biological limit, when
the cause of death and feeblemindedness is not a certain disease which can be conquered, but
general deterioration of the entire organism, its decay on the cellular level, when the cells stop
to divide. A live cell is a very complex biological formation. In its nucleus it has DNA -
biological molecules consisting of tens of thousands of atoms connected between themselves
with very fragile molecular links. Suffice it to say, that temperature fluctuation of only a few
degrees can ruin these links. That is why a human organism maintains a certain temperature -
36.7 C. Raising this temperature only 2-3 degrees causes pain, and 5-7 degrees leads to death.
Maintaining the existence of human cells also presents a big problem for humanity involving
food, shelter, clothes and ecologically clean environment.
Nevertheless, human cells cannot exist eternally even under ideal conditions. This
follows from the atomic-molecular theory. Atoms of biological molecules permanently
oscillate and interact with each other. According to the theory of probability, sooner or later
the impulses of adjacent atoms influencing the given atom, add up, and the atom acquires
enough speed to break loose from its atomic chain, or at least to transfer into the adjacent
position (physicists say that the impulse received by the atom has surpassed the energy
threshold which retains the atom in in its particular place in the molecular chain). It also
means that the cell containing this atom has been damaged and cannot any longer function
normally. Thus, for example, we get cancer cells which cannot fulfill their designated
functions any more and begin to proliferate abnormally fast and ruin human organs.
This process accelerates manifold when a person has been exposed to a strong
electromagnetic radiation, for instance, Roentgen or Y-rays, a high-frequency electric current
or radioactive materials.
Actually, the process of deforming of the hereditary DNA molecule under the influence
of weak cosmic rays can take place from time to time, leading sometimes to birth defects, or
it may turn out to be useful for the survival properties. And this plays a positive role for a
particular species of plants or animals contributing to their adaptability to the changed
environment and their survival as a species. But for a particular individual such aberration is a
tragedy as a rule, since the overwhelming majority of such cases are birth defects, with only
few cases of useful mutations. And human society in general is suspicious of people who are
radically different in their looks or abilities.
New Concepts, Ideas and Innovations in Aerospace… 385
AN UNEXPECTED BREAKTHROUGH
An unusually fast development of computer technology, especially the microchips which
allow hundreds of thousands of electronic elements on one square centimeter, has opened
before the humanity a radically different method of solving the problem of immortality of a
separate individual. This method is based not on trying to preserve the fragile biological
molecules, but on the transition to the artificial semiconductive (silicone, helium, etc.) chips
which are resistant to considerable temperature fluctuations and do not need food or oxygen
and can be preserved for thousands of years. And, most important, the information contained
in them can easily be re-recorded into another chip and be stored in several duplicates.
And if our brain consisted of such chips, and not the biological molecules, then it would
mean that we have achieved immortality. Then our biological body would become a heavy
burden. It suffers from cold and hot temperatures, needs clothes and care, can be easily
damaged. It‘s much more convenient to have metal arms and legs, tremendously strong, and
which are insensitive to heat and cold and do not need food or oxygen. And even if they
break, it‘s no big deal - we can buy new ones, more improved.
It may seem that this immortal man does not have anything human (in our understanding)
left in him. But he does, he has the most important thing left - his consciousness, his memory,
concepts and habits, i.e. everything encoded in his brain. Outwardly, he can look quite
human, and even more graceful: a beautiful young face, a slim figure, soft smooth skin, etc.
Moreover, one can change the look at will, according to current fashion, personal taste and
the individual understanding of beauty. We are spending huge amounts of money on
medicine. If we had been spending at least one-tenth of this money on the development of
electronics, we would get immortality in the near future.
According to the author‘s research, such transition to immortality (E-creatures) will be
possible in 10-20 years. At first it will cost several million dollars and will be affordable only
to very wealthy people, important statesmen, and celebrities. But in another 10-20 years, i.e.
in the years 2030 - 2045, the cost of HEC (human-equivalent chip), together with the E-body,
and organs of reception and communication, will drop to a few thousand dollars, and
immortality will become affordable to the majority of the population of the developed
countries, and another 10-15 years later, it will be accessible to practically all inhabitants of
the Earth. Especially when at first it will be possible to record on chips only the contents of
the brain, and provide the body for its independent existence later.
On October 11, 1995, Literaturnaya Gazeta (The Literary Gazette, a popular Russian
weekly) published my article "If Not We, Then Our Children Will Be The Last Generation Of
Human Beings" devoted to electronic civilization. The editor Oleg Moroz reciprocated with
the article "Isn‘t It High Time To Smash Computers With a Hammer?" (November 22, 1995)
in which he discussed the ethical side of annihilating rational electronic creatures to preserve
humanity. But if the cost of the HEC drops and the procedure of reincarnation into the Ecreature
before death (transition to immortality) for the majority of people becomes
affordable, then the situation deserves a second look. Indeed, the first to perform such
transition will be very old or incurably sick people. And to pummel computers with a hammer
will be equal to killing one‘s own parents and precluding one‘s own possibility to become
immortal.
386 Alexander Bolonkin
Once, the host of an American television program whose guest I was, asked me, "Will the
electronic creature be entirely identical to its parent, with his feelings and emotions?" The
answer was, "At first - yes!" But the development of these creatures will be so fast that we
cannot really foresee the consequences. If a biological human being needs dozens of years to
learn science, foreign languages, etc., an E-creature will acquire this knowledge in fractions
of a second (the time needed to record it in its memory). And we know how different collegeeducated
people are from, say, pre-schoolers, in their cognizance. And, since the first Ecreatures
will be contemporary middle-aged people who will, at least initially, preserve their
feelings towards their children (contemporary younger generation), in all probability, there
won‘t be a mass destruction of humans by E-creatures. For some time they will co-exist. It‘s
quite likely that the birthrate of humans will be curtailed or it will be dropping due to natural
causes, and the living, as they become old, will be transforming themselves into E-creatures.
That is to say that the number of E-creatures will be growing and the number of people
diminishing, till it gets to the minimum necessary for the zoos and small reservations. In all
likelihood, the feelings that E-creatures may have towards humans as their ancestors, will be
fading away, in proportion to the growing gap between the mental capacity of humans and
electronic creatures, till they become comparable to our own attitude towards apes or even
bugs.
Figure 1. Robot.
Another thing is quite obvious, too - that biological propagation will be so expensive,
time-consuming, and primitive, that it will go into oblivion. Each E-creature can reproduce
New Concepts, Ideas and Innovations in Aerospace… 387
itself simply by re-recording the contents of its brain to a new E-creature, i.e. propagate
practically instantaneously, bypassing the stages of childhood, growing up, education,
accumulating experience, etc. But, of course, this mature "offspring" will be completely
identical to its parent only at the first moment of its existence. In time, depending on the
received information and the area of expertise, this E-creature will be alienating itself from its
ancestor, and, possibly, even become his enemy at some point, if their interests cross or go in
opposite directions.
CONTEMPORARY RESEARCH
The cognitive abilities of man are defined by his brain, to be precise, by ten billion
neurons of his brain. Neurons can be modeled on the computer. Such experiments have been
conducted by Professor Kwin Warwick, head of the cybernetics department of Reading
University in the south of England, one of the biggest specialists in robot technology in the
world. The results of these experiments were presented at the International Conference on
Robotics. Professor Warwick has created a group of autonomous self-propelled miniature
robots which he called "the seven dwarfs."
A group of scientists headed by Rodney Brook from the laboratory of artificial
intelligence of MIT, are working on an unusual project which they called "Cog." The
researchers want to model the mental and physical capacity of a six-month old. Their robot
has eyes, ears, hands, fingers, an electronic brain and a system of information transmission
duplicating human nervous system. By this kind of modeling, the researchers want to gain
better understanding of how human beings coordinate their movements, how they learn to
interact with the environment. The realization of this program will take ten years and will cost
several million dollars.
They have already built a couple dozen humanoid robots which are moving autonomous
machines with artificial intelligence. They are capable, through the sensors, to receive
information about the environment, generalize, and plan their actions and behavior. Thus, for
example, if a robot‘s leg bumps against an obstacle and receives a blow, the robot acquires a
reflex to withdraw it quickly. They have already developed several dozen of such reflexes in
their behavior, which helps them to safeguard and protect themselves.
Brook says that in the course of human evolution, the human brain has developed
thousands of conventional solutions to everyday problems such as optical and audio
discerning and movement. All this needs to be studied. One cannot instantly transform a bug
into a man. That is why our program will take ten years. I will consider my work completed
when I create the smartest cat in the world.
It should be noted that the most powerful supercomputer can only model 40-60 million
neurons, i.e. it is 200-300 times weaker than a human brain. But this gap will be overcome in
the near 3-5 years ( In December 1996 the "Intel" company created a computer whose power
equals one teraflops. It cost 55 million dollars).
Not long ago "The Russian Advertisement" newspaper re-printed the article of Igor
Tsaryov first published in the newspaper "It‘s Hard to Believe." He writes that for several
years the U.S. Ministry of Defense has been secretly working on a unique project "The
Computer Maugli" (Sid). When a thirty-three year old Nadine M. gave birth to a boy, the
388 Alexander Bolonkin
doctors established that he was doomed. He was on a life support for a few days. During that
time his brain was scanned with special equipment, and the electric potential of the neurons of
this brain was copied into the neuron models in the computer. Steem(?) Roiler, one of the
participants of this project, said at the computer conference in Las Vegas that they had
managed to scan 60% of the infant‘s neurons. And this small artificial brain began to live and
develop. First only his mother was informed. She took it calmly. The father was horrified at
first and tried to destroy this computer creature. But later both parents started treating him as
a real child. The computer was connected to the multi-media and virtual reality systems.
These systems allow not only to have a three-dimensional full-sized image of Sid, but also to
hear his voice, communicate with him, and "virtually" hold him in hands, so to speak. But
when a special committee decided to open some results of the project, and "The Scientific
Observer" published some data, one of American computer whiz-kids managed to decipher
the secret code and copy some files. Sid got a defective "twin." Fortunately, the whiz was
quickly found, and the first in human history attempt to steal electronic children and
duplicating copies of electronic creatures, was severed. At the present time, both parents take
care of their "child‘s" health and demand that the researchers install up-to-date programs of
defense from computer viruses and burglars.
Unfortunately, and I am sure they have reasons for that, Americans keep secret the
important details and results of the project - for instance, how they copied the potentials of the
neurons, how the first E-creature is developing, what are the conclusions of the scientists.
And probably, they are right, not willing to let the genie out of the bottle. More so because
modern virtual reality systems are able to create false objects, e.g. model the image of any
dead person or leader. It is possible to show on television how he is making a speech today,
has a press-conference, talks to people, spends time with his family, etc.
But one cannot keep any secret for long, especially in science. The very possibility of a
breakthrough stimulates other scientists and other countries to work in this direction. And
sooner or later, the results will be repeated. Let‘s remember, for instance, that there haven‘t
been a bigger secret than the production of an A- or H-bomb. But more and more countries
re-invent them, gain expertise in nuclear technology and start producing their own nuclear
weapons.
INTELLIGENCE IN SPACE
Since E-creatures will be made of super-strong steels and alloys, their brain will be
working on radio-active batteries, and power will be supplied by compact nuclear reactors,
they will not need air, warmth, water, food, clothes, shelter, good quality environment, etc.,
which is the main concern of humanity and consumes 99.9% of its time and energy. This also
means that E-creatures will be able to travel freely in the desert, the Arctic and the Antarctic
regions, sub-atmosphere, mountain summits, the bottom of the ocean. They will be able to
live, work and travel in space, receiving their energy directly from the sun.
Besides, as organs of feelings, E-creatures can use the whole arsenal of highly sensitive
apparatuses created by the civilization, i.e. not only the visible light and sound, but also
radiolocation, infra-red, ultra-violet, roentgen and Y-rays, ultra- and infra-sounds,
New Concepts, Ideas and Innovations in Aerospace… 389
audiolocation, environment sensors, etc. All this information can be received instantly
through radio, satellite and cable network.
Moreover, since E-creatures (just like humans, for that matter) are nothing else but
information recorded in their brains, and re-recording of this information from one chip to
another (unlike human reproduction) does not present any difficulty and can be realized
through radio, cable network, or a laser beam, they can travel on Earth, as well as in outer
space, without their actual physical movement, simply by re-recording the contents of their
brains into the chips on the Moon, Mars, or Jupiter.
Which is to say that E-creatures will have the ability to move EXTRA-CORPORALLY
with the speed of light - the maximal possible speed in the material world. This will be,
indeed, like an incorporeal soul which can travel, so to speak, from one body to another, or, to
be more exact, from one chip to another.
The expansion of E-creatures (E-civilization), first in the solar system, then in our galaxy,
then in the entire Universe, will be fast. To achieve this, it is not necessary to launch huge
spacecraft with a large crew, as it is depicted in science-fiction books. It will be enough to
send a receiver to this or that part of the Universe, which will receive information and reproduce
E-creatures. Then the speed of the expansion of E-civilization on some planet will
depend only on the rate of production of robots and chips, and the speed of the transmission
of information. It is quite obvious that the reproduction of E-creatures will take place in
geometric progression and will only be limited by the natural resources of the planet.
Thus E-creatures realize in practice the idea of EXTRA-CORPORAL travel with the
speed of light. Why, indeed, should an E-creature travel hundreds or thousands of years to a
certain planet, when, with the help of a laser beam, it can transmit with the speed of light, all
the information stored in his brain, to another chip, on another planet.
And if a planet were to meet with an ultimate catastrophe, like a collision with a huge
meteorite, another planet, or the explosion of the sun, E-civilization can arrange transporting
E-creatures to another planet or another solar system.
One more thing is of interest. A light beam can travel to other galaxies for millions of
years, so this, in a manner of speaking, "incorporeal soul" can exist for millions of years as an
electromagnetic field and "resurrect" as an E-creature through a receiver. This can occur even
without a special receiver, as the high energy electromagnetic oscillations can yield material
particles, and their energy (frequency) increases the closer it gets to a strong gravitational
field, e.g. near a "black hole." And since it will not be hard for an E-creature to produce a
DNA molecule, it means that it will not be hard for it to bring biological life to any suitable
planet and control and develop it in the necessary direction, for example, to create a human
being.
REFERENCES
The twenty-first century: the advent of the non-biological civilization and the future of the
human race. The scientific journal "Kybernetes", Vol.28 No.3,1999, pp.325-334,@MCB
University Press, 0368-492X), (English).
390 Alexander Bolonkin
Bolonkin A.A., The twenty-first century – the beginning of human immortality, Journal
Kybernetes, Vol. 33, No, 9/10, 2004, pp.1535-1542, Emerald Group Publishing Limited
0368=482X. (English).
Bolonkin A.A., Human Immortality and Electronic Civilization. Electronic book, 1993.
WEB: http://Bolonkin.narod.ru, http://Bolonkin.narod.ru/p101.htm (English),
http://Bolonkin.narod.ru/p100.htm (Russian).
There are a lot of my articles about this topic on Russian. Some of them in book (1993)
http://Bolonkin.narod.ru/p100.htm
Chapter 3
SCIENCE, SOUL, PARADISE, AND ARTIFICIAL
INTELLIGENCE
ABSTRACT
Discussing the problem science, soul, paradise, and artificial intelligence. It is shown
that the soul is only knowledge in our brain. To save the soul is to save this knowledge.
ADVANTAGES OF ELECTRONIC BEING
It was shown in my articles about the artificial intelligence and human immortality that
the issue of immortality can be solved fundamentally only with the help of changing a
biological bubble of a human being to an artificial one. Such an immortal person made of
chips and super strong materials (the e-man, as it was called in my articles) will have
incredible advantages in comparison with common people. An e-man will need no food, no
dwelling, no air, no sleep, no rest, no ecologically pure environment. Such a being will be
able to travel into space, or walk on the sea floor with no aqualungs. His mental abilities and
capacities will increase millions times. It will be possible to move such a person at a huge
distance at a light speed. The information of one person like that could be transported to
another planet with a laser and then placed in another body.
Such people will not be awkward robots made of steel. An artificial person will have an
opportunity to choose his or her face, body, good skin. It will also be possible for them to
reproduce themselves avoiding the periods of childhood, adolescence, as well as education. It
will not be possible to destroy an artificial person with any kind of weapons, since it will be
possible to copy the information of his mind and then keep it separately.
I have received tons of responses and comments since my first articles about this subject
were published in 1994. Below I will try to answer the most important ones of them.
392 Alexander Bolonkin
HUMAN SOUL
A lot of people, especially those, who believe in God, are certain that a biological human
being has a soul. This is something that an artificial man will never have. No person can
explain the meaning of the word ―soul.‖ They just keep saying that a human soul is not
material, and that it leaves a person‘s body after death and flies either to paradise or to hell.
Let‘s try to analyze the notion of a soul from the scientific point of view.
First of all, a soul is supposed to remember its past life, its relatives and friends. It is also
supposed to preserve its emotions to them, to care about them and recognize them, when they
come to heaven. No one would need a soul that does not remember anything. This means that
a soul is a human being without a body. In other words, a soul is the information that is kept
in a human mind - his memories, knowledge, skills, habits, conduct programs, emotions and
feelings, ides and thoughts, and so on. If we learn how to move this information onto other
carriers, we will be able to move a person‘s soul to other bubbles and to keep it there for an
unrestricted period of time. As it is well known, information is virtual, i.e. it satisfies another
human soul feature – a non-material quality. Man‘s new bubbles can be both artificial and
biological. A soul (a complex of knowledge and information) can be rewritten into a clone of
that same person. To put it otherwise, a person will live forever biologically as well, moving
from old bubbles to new ones. It would be also possible to move a soul to artificial bodies,
which possess all those qualities that we mentioned above. Furthermore, information (a soul)
could be radiated in the form of electromagnetic waves. These waves can be spread in the
universe at the light speed. They can travel around the universe for thousands of years,
reaching its most distant parts. People see the star light that was radiated millions of years
ago. This means that our immaterial soul can live in the universe in the form of
electromagnetic radiation and then revive in millions of years.
Some of my readers wrote that an old brain can go corrupt and die, when moving a
human soul from one body to another one. If it does not go corrupt, this inner self will die
anyway, when an old biological bubble is not able to function normally anymore. Let us try to
find out, what that inner self is. The majority of people identify their inner selves with their
own bodies. I believe that the inner self is the information, which is kept in our mind. It is our
soul. Every day we go to sleep. However, our brain does not stop working at night. Every
time we wake up, we have our inner self changed. We ―die‖ when we fall asleep and then
―resurrect‖ when we wake up. This means that recording the information from a human brain
will mean nothing but moving it to another bubble. Heaven on Earth.
A reporter from the newspaper ―Argumenty i Fakty‖ (―Arguments and Facts‖) sent me
the following letter:
―Dear Mr. Bolonkin. Needless to mention that it is great to live forever. However, I have
a question, which you can guess from a well-known Soviet joke. ―A guy is going to join the
communist party. A committee asks him: - Will you stop drinking? - Yes, I will. - Will you
quit smoking? - Yes I will. - Will you stop loving other women? - Yes, I will. - Will you die
for the Communist Party of the Soviet Union, if there is such a need? - Yes, I will. To hell
with this life.‖
Here is my answer:
New Concepts, Ideas and Innovations in Aerospace… 393
―You do not need to worry that living in an electronic form will be dull and boring. It is
vice versa, actually. When the information will be recorded onto other carriers, all human
emotions, feelings and so on will also be carried over and preserved. In addition to that, the
copies of certain emotions, pleasures, fears and so forth will be possible to record separately.
After that, those separately recorded emotions and feelings can be given or sold to other
people. Other e-men will have an opportunity to enjoy sex with a beauty queen, to experience
the enjoyment of a sports victory, to take pleasure of power and the like. All modern art is
based on artists‘ aspiration to transcend their emotions, to make other people feel, what
characters feel. Those works of art, which make that happen best, are considered to be
outstanding and great. Electronic people will get those emotions directly. To crown it all, it
will be possible to intensify those emotions, as we intensify a singer‘s voice now. Electronic
people will have a huge world of all kinds of pleasures; it will be possible to know, what a
dictator or an animal feels. I think that an e-man‘s pleasure time will be limited legally, for the
civilization‘s progress will stop otherwise. For the time being, the authorities prohibit drug
addiction in order not to let the society degrade.‖
A soul‘s living in such a virtual world will have all pleasures imaginable. It will be like
living in paradise, as all religions see it. Computer chips of our time possess the frequency of
more than two billion hertz. However, a human brain reacts to a change of environment only
in one-twentieth of a second. This means that one year of life on Earth is equal to 100 million
years of a soul‘s living in the virtual world (paradise). Living in the virtual world will not be
distinguishable from the real life. It will have a lot more advantages: you will have an
opportunity to choose a palace to live in, you will have everything that you might wish for.
Yet, living in hell also becomes real. There is a hope that the ability to keep souls alive will
be achieved by highly-civilized countries first. In this case they will prohibit torturing sinners,
as they prohibit torturing criminals nowadays. Furthermore, criminal investigations will be
simplified a lot, judicial mistakes will be excluded. It will be possible to access a soul‘s
consciousness and see every little detail of this or that action. Sooner or later religious
teachings about soul, heaven and hell will become real. However, all that will be created by
man.
The so-called end of the world will also have a chance to become real, though. The
religious interpretation of this notion implies the end of existence for all biological people
(moving all souls onto artificial carriers, either to heaven or to hell). However, in difference to
religious predictions, this process is going to be gradual.
THE SUPREME MIND AND MANKIND’S EXISTENCE
I set forth an idea in my first publications that the goal of the mankind‘s existence is to
create the Supreme Mind and to keep this Mind forever, no matter what might happen in the
universe. The biological mankind is only a small step on the way to the creation of the
Supreme Mind. The nature found a very good way to create the Supreme Mind: it decided to
create a week and imperfect biological mind at first. It took the nature millions of years to do
that. The twentieth century was a very remarkable period in the history of the humanity.
There has been incredible progress achieved, like never before. The scientific and the
technological level of the humanity became sufficient for the creation of the artificial
intelligence. This will be the first level of the Supreme Mind, when the human mind will
394 Alexander Bolonkin
make a step towards immortality. At present moment we stand on the edge of this process. It
is obvious that biological people will not be able to compete with e-men by the end of this
period. Common people will not be able to learn the knowledge that electronic people will
get. The new cyberworld will be the only way for a human mind to survive. Feeble and
unstable biological elements in a mind carrier or in its bubble will reduce its abilities and
capacities a lot. If a common person will be willing to become a cyberman, then this
cyberman will be more willing to get rid of all biological elements in his system and become
like everyone. For example, there are no people in our present society, who would agree to
become a monkey again.
The Supreme Mind will eventually reach immense power. It will be able to move all over
the universe, to control and use its laws. It will become God, if the notion of God implies
something that knows and does everything. In other words, Man will become God. Yet, it
does not mean that this will be the time, when the Supreme Mind will start dealing with
human problems. For instance, ants and people have a common ancestor. A human being is
God against ants. A man can destroy a huge city of ants (an anthill, in which hundreds of
thousands of ants live) just with one kick. Ants will perceive this as an immense natural
disaster, since they can see at the distance of only one centimeter. I do not know anyone, who
would deal with charitable activities for ants. Everything that a man can do is to bring ants to
a deserted island and give them an opportunity to reproduce themselves.
Figure 1. Robot in street.
ESSENTIAL STATE OF THINGS AND PERSPECTIVES
A lot of people will say that it is just a fantasy. This is a very convenient way to cast all
that aside, until it starts happening. This is exactly what happened before the invention of a
plane or a computer. It took 50 years to increase computer‘s memory 100 million times. It
New Concepts, Ideas and Innovations in Aerospace… 395
would be possible to start working on the creation of the Supreme Mind, if there were a
computer that would be capable of running a thousand billion of operations during only one
second. In 1994 I said that such a super computer will be invented in the year 2000. I was
wrong, for it appeared at the end of 1998. There is also a need of a self-developing program
that would be capable of adjusting itself to constantly-changing circumstances. A human
child does not develop and grow at once. A child has to study for about 20 years, to learn
from his parents and friends, to have relations with nature and other people in order to gain
more and more experience, to come to realization of his or her inner self. Unfortunately, the
science of the artificial intelligence has chosen a wrong way of its development from the very
start. Scientists tried to develop programs, which would react to certain external signals. In
other words, people started working on robots that would cope with certain problems. A lot of
efforts have been spent to discover the peculiarities of human speech, for instance. Some of
those scientific works are absolutely no use for the electronic mind. It is easier for e-men to
communicate with the help of their own electronic language, to recognize objects not by their
images, but by way of measuring their speed, weight, composition and so on. All of that can
be done at a distance. Biologists and physicists have spent decades for those useless works.
They believe that one should study brain activities, find out the way it works and thinks. Then
it would be time for modeling it with the help of a computer. This is a wrong way to go as
well. A human brain is very complicated, it is very hard to study its activities. More
importantly, even if we learn how it works, it would not mean that the method would be good
for a computer. Here are some examples to prove it. Hundreds of years ago people were
longing to learn how to fly. They saw that bird waved its wings for flying, so they tried to
model such wings, to wave them, and to take off. However, people could fly up into the sky
only when they developed still wings and propellers. A waving wing was absolutely not good
for technology, the same way as a propeller is not good for the wild nature. In addition to that,
planes with still wings fly a lot faster than birds. Another example: ancient people always
wanted to run as fast as four-legged animals. Now everyone knows that no one uses machines
that would move with the help of legs. Legs were changed with wheels – something that has
never been used by the natural world.
In 1998 I suggested people should lay new principles as the foundation of artificial
intelligence program. Those principles would be: to realize the goal of existence, to study the
environment (everything that goes separately from the ―inner self‖), to model environment, to
predict actions‘ results, to counteract with the environment in order to achieve temporal and
global goals, to correct modeled environment, actions and their results according to the results
of such counteraction. Unfortunately, I had to deal with the fact that everyone refused to
realize and understand those principles. First of all, everyone believed that since the ―virtual
ego‖ does not have a human body, it would never have any rights. They said that it would be
possible to control such an e-man completely and then to kill him (erase his soul from the
computer memory). I wonder, what they would do, if they were offered to kill their relatives‘
souls that way? People link their body and soul together, and there is no way around that.
They are ready to struggle for the rights of every living being, but they never want to accept
the rights of a program or of a computer memory. Second of all, people want an artificial
intelligence to give smart answers to their questions that can be rather stupid at times. They
do not need smart answers from babies. They are always ready to stand all stupid things that
children do for years. Instead, they try to teach them everything. Yet, they want a new
artificial mind to give bright answers without any education. To crown it all, people want a
396 Alexander Bolonkin
computer to speak their human language, which is absolutely alien for a machine. Can you
imagine that a person will have to answer the questions of an alien in Maya‘s language? Let‘s
assume that a representative of an electronic civilization came to planet Earth in order to find
out, if there are reasonable creatures living on it. This e-man suggested a common biological
man to multiply 53758210967 by 146, then divide it by 50, deduct 968321 from it and
calculate the hyperbolic sine. A computer would give the correct result of this sum in less
than a second. A man would spend really a long time on that, making numerous mistakes.
However, it would not be correct to say that a computer is smart and a man isn‘t.
Religious figures show a strong resistance to these ideas. It stands the reason that they all
think that the creation of the Supreme Mind, immortality ideas are blasphemous.
Unfortunately, the church has already blocked such decisions as human cloning, increasing
the productivity of plants by means of changing their genes. It should be mentioned here that
human cloning does not solve the questions of immortality. A clone is a copy of its biological
bubble. A clone inherits the biological advantages of a bubble, for example, a singer‘s fine
voice, an athlete‘s strength and the like. A clone will never inherit its‘ copy‘s soul. Therefore,
human cloning is only an illusion of immortality. It can be a wonderful way to improve the
biological bubble of a human being. Moving a human soul onto other carriers is a very
complicated issue. People learned to see, which brain areas get activated, when a person
remembers something, or tries to solve this or that question. We also learned to penetrate into
certain neurons and record their impulses. To my mind, physiologists chose a wrong way here
as well, when they tried to model brain activities. A human brain is an analogue of a huge
state with a ten billion strong population. There is no use to ask each citizen of that country,
what he or she is doing at the moment. One has to copy the database of this state, in order to
copy its work. The easiest way to do so is to penetrate into informational channels of its
supreme body (the ―government‖), on the inquiry of which the brain presents any information
and allows to record its data on a disk, for instance. It is possible to do that, for the supreme
brain area constantly extracts the necessary knowledge and programs according to our
activities. So, we would need to send ―intelligent officers‖ to the brain so that they could get a
copy of this state or get connected to its major information channels.
Another way to do that is to record all incoming and outgoing information, which comes
to/from a person, to record his or her emotions and reactions. An English-speaking reader,
who reviewed one of my English articles once told me: ―Your English is not perfect. You
should find an English-speaking co-author. It is better to have a half of a pie than nothing at
all.‖
HOPE
I do not doubt that the electronic civilization era, the era of the Supreme Mind and
immortality will be achieved sooner or later. Those people, who have little in common with
science, are drawn to believe that everything depends on scientists. They think that scientists
can solve any problem, if they deal with it profoundly. As a matter of fact, everything
depends on state and military officials. Sometimes, they know nothing of scientific
perspectives and innovations. Scientists are like qualified workers. They need to get paid,
they need to work with fine equipment. They will work only if they are get paid for it. Even if
New Concepts, Ideas and Innovations in Aerospace… 397
a scientist will have a wish to do something perspective during his free time, he will have no
necessary equipment for that. Even such powerful companies as IBM, Boeing, Ford and
others are interested only in the applied research, which does not require large investments.
The major goal of such research is to give a maximum profit to this or that company. A
fundamental research, the discoveries that are important for the whole humanity, not just for a
company, might be of interest to a bright government. It goes without saying that a bright
government is so hard to find. Every government is interested in the military power of its
country. It is ready to fund defense technology works and military innovations. Von Braun
convinced Hitler of real perspectives for missiles, WWII was followed with an arm race. This
eventually led to space achievements and other kinds of technical progress of the humanity.
The USA won the Moon race and stopped flying there 30 years ago. America keeps cutting
its space research assignments every year. There are no serious assignments in the world for
the invention of either the Supreme Mind or the artificial intelligence. Yet, they are most
important and perspective problems of the humanity. The computers that we have at present
are used for modeling nuclear weapons and sometimes, weather. Furthermore, the mankind
does not spend much time thinking over the reason and goal of its existence. People spend a
lot of their efforts and funds for solving local, temporal problems. Huge money and efforts
are spent on conflicts and wars.
A certain hope has appeared recently. As experience shows, unmanned planes are a lot
cheaper than piloted warplanes. More importantly, unmanned plane crashes do not cause
harsh public reactions in civilized countries as pilots‘ or soldiers‘ deaths. The Americans
design such planes successfully, but the planes are controlled by an operator within the USA.
It has been proved that this remote control is not good for unmanned planes. The USA has
missed Bin Laden and Omar in Afghanistan several times, two Iraqi pursuit planes downed an
unmanned Predator in the Iraqi airspace. An unmanned plane can become something valuable
indeed, if it has an artificial intelligence, if it is capable of recognizing and destroying targets
itself. The Pentagon has assigned certain money for the research of this issue. It is a very hard
goal to pursue (to create the mind of a pilot), but it is a very perspective one. In this case there
would be no need to eliminate the young part of a country‘s population, if robots could
conduct the warfare.
I suggested the hierarchical structure of an artificial intelligence, on the ground of which
the real brain probably works. Let us imagine a state with a dictator at the head. A dictator
would never be able to find efficient solutions for external and internal state problems. A
dictator has ministries, which are then divided into divisions and departments. This forms a
pyramid, in which all departments have their own databases, as well as the access to the
common base. All divisions are busy with their particular problems, in accordance with the
dictator‘s ideology. A dictator only sets problems up, while adequate divisions suggest
solutions. For example, a man decides to cross a road with a heavy traffic. He looks at the
road, while adequate parts of his brain automatically receive the information about the width
of the road, the distance to nearest cars, their speed, and so on. The brain automatically makes
adequate calculations, which eventually lead to the final decision: when it is safe to cross the
road. All kinds of enlightenment in the solution of a problem are simply considered to be the
―help from above.‖ However, this is nothing, but the joint work of that pyramid. Human
beings do not even know that such a pyramid exists. Pyramid‘s decisions are based on the
knowledge of a certain individual. If an individual knows absolutely nothing about the
quantum theory, he will never solve any of its problems. Therefore, an artificial intelligence
398 Alexander Bolonkin
of a high level cannot be realized with a personal computer that has only one chip and a
successive work order.
My scheme stipulates the distribution of functions between parallel chips. The top one of
them is offered to deal only with solution variants, their estimation and choice.
Every human being wants to extend his or her life. This can be seen from everyone‘s
wish to have children, or to do something outstanding. It is simply enough to avoid danger
sometimes. Even suicidal terrorists believe that they will go to heaven, when they kill
themselves. The most important problem that the humanity has is the problem of immortality.
Let us hope that it will be solved in the future.
REFERENCES
Bolonkin A.A., The twenty-first century: the advent of the non-biological civilization and the
future of the human race, Kybernetes, Vol.28, No3,1999, pp.325-334, MCB University
Press, 0368-492X (English).
Bolonkin A.A., Twenty-fist century – the beginning of human immortality, Journal
―Kybernetes‖, Vol.33, Mo. 9/10, 2004, pp.1535-1542, Emerald Press,
www.emeraldinsight.com/ISSN 036-492X.htm (English)
Bolonkin A.A., Human Immortality and Electronic Civilization. Electronic book, 1993.
WEB: http://Bolonkin.narod.ru, http://Bolonkin.narod.ru/p101.htm (English),
http://Bolonkin.narod.ru/p100.htm (Russian).
Bolonkin A.A., Human Immortality and Electronic Civilization, Lulu, 3-rd Edition, 2007,
(English and Russian), 66 pgs. http://www.lulu.com search ―Bolonkin‖.
Chapter 4
BREAKTHROUGH TO IMMORTALITY
ABSTRACT
The author offers a new method for re-writing the human brain on electronic chips.
This method allows for the modeling of a human soul in order to achieve immortality.
This method does not damage the brain but works to extend and enhance it.
1. BRIEF DESCRIPTION OF PREVIOUS WORKS
BY THE AUTHOR
In a series of earlier articles (see referenced list at the end) the author shows that the
purpose of Nature is to create Super Intelligence (SI). With its ability to understand the
Universe, advanced entities with SI Power will be able to survive major cataclysms. There is
the Law of Increasing Complexity (in opposition to the Entropy Law – increasing chaos).
This Law created biological intelligence (people). Human have since became a sovereign
entity on the Earth and in Nature above all other creatures.
However, humans are just as mortal as any other biological creature. The human brain
and body include albumen, molecules containing tens of thousands of atoms united by weak
molecular connections. A change of only a few degrees in temperature results in death. The
human biological brain and body require food, water, oxygen, dwelling, good temperature
and environment in order to survive. These conditions are absent on most other planets. This
makes it difficult for humans to explore Space or settle on other planets. Humanity losses
valuable information (human experience) with old age and death, and humans invest
considerable time and money toward raising and teaching children.
2. ELECTRONIC IMMORTALITY
ADVANTAGES OF ELECTRONIC EXISTENCE
In earlier works the author has shown that the problem of immortality can be solved only
by changing the biological human into an artificial form. Such an immortal person made of
400 Alexander Bolonkin
chips and super-solid material (the e-man, as was called in earlier articles) will have
incredible advantages in comparison to conventional people. An E-man will need no food, no
dwelling, no air, no sleep, no rest, and no ecologically pure environment. His brain will work
from radio-isotopic batteries (which will work for decades) and muscles that will work on
small nuclear engines. Such a being will be able to travel into space and walk on the sea floor
with no aqualungs. He will change his face and figure. He will have super-human strength
and communicate easily over long distances to gain vast amounts of knowledge in seconds
(by re-writing his brain). His mental abilities and capacities will increase millions of times. It
will be possible for such a person to travel huge distances at the speed of light. The
information of one person like this could be transported to other planets with a laser beam and
then placed in a new body.
Such people will not be awkward robots as in the movies. An artificial person will have
the opportunity to choose his or her face, body and skin. It will also be possible for them to
reproduce and then avoid any period of adolescence including the need for education. It will
be impossible to destroy this entity with any kind of weapons, since it will be possible to copy
the information of their minds and than keep such information backed up in separate distant
locations. As was written in the science fiction book, ―The Price of Immortality”, by Igor
Getmansky (Moscow, Publish House ECSMO, 2003, Russian) an artificial person will have
all of these super-human abilities.
3. WHAT ARE MEN AND INTELLIGENT BEINGS?
All intelligent creatures have two main components: 1. Information about their
environment, about their experience of interacting with nature, people, society (soul) and 2.
Capsule (shell), where this information is located (biological brain, body). The capsule
supports existence and stores information and programs for all of its operations. The capsule
also allows the creature to acquire different sensory information (eyes, ear, nose, tongue and
touch) and it moves to different locations in order to interact with the environment.
The main component of an intelligent being is information (soul). The experiences and
knowledge accumulated in the soul allows the entity to interact more efficiently in nature in
order to survive. If the being has more information and better operational programs (ability to
find good solutions), then it is more likely thrive.
For an intelligent being to save its soul it must solve the problem of individual
immortality. Currently man creates a soul for himself by acquiring knowledge from parents,
educational systems, employment and life experiences. When he dies, most knowledge is lost
except for a very small part which is left through works, children and apprentices. Billions of
people have lived on Earth, however, we know comparatively little about ancient history.
Only after the invention of written language did people have the capacity to easily save
knowledge and pass it on to the next generation.
As discussed earlier, the biological storage (human brain) of our soul (information) is
unreliable. The brain is difficult to maintain and requires food, lodging, clothes, a good
environment and education, etc. To support the brain and body, humans spend about 99% of
their time and energy, and eventually what knowledge is gained is taken to the grave in death.
New Concepts, Ideas and Innovations in Aerospace… 401
There is only one solution to this problem – re-write all of the brain information (our
soul) in more strongly based storage. We must also give the soul the possibility to acquire and
manipulate information from the world. This means we must give sensors to the soul so it
may have communication and contact with people and other intelligent beings. We must give
the soul a mobile system (for example, legs), systems for working (hands), etc. thus giving
the soul a new body in which to LIVE.
The reader may ask - these ideas seem interesting, but how does one we re-write a human
soul to live within a new carrier, for example, in electronic chips?
4. THE MAIN PROBLEM WITH ELECTRONIC IMMORTALITY –
RE-WRITING BRAIN INFORMATION (SOUL) TO ELECTRONIC CHIPS
IS THAT IT’S IMPOSSIBLE TO DO THIS WITH CURRENT TECHNOLOGY
At present scientists are working to solve this problem. They know that the brain has
about 15 billion neurons, and every neuron has about ten connections to neighboring neurons.
Neurons gain signals from neighboring neurons, produce signals and then send these signals
to others neurons. As a result, humans are able to think and find solutions. On the bases of
this way of thinking, humans can come to solutions without exact data. (Concepts of brain
were described in my previous articles. For example, see ―Locate God in Computer-Internet
Networks‖ or ―Science, Soul, Heaven and Supreme Mind‖. See also my articles on the
Internet and references at end of this article.).
Scientists are learning how to take individual neurons on micro-electrodes and record
their impulses. The ideas of scientists are very simple - study how single neurons and small
neuronal network work and then model them by computer. They hypothesize that if we can
model 15 billion neurons in a computer they will learn how the brain works, and then they
will have Artificial Intelligence equaling the human brain.
In my previous work I show this as a dead-end direction for Human Immortality. It‘s true
that we‘ll create an Artificial Intelligence (AI) that will be more powerful than the human
mind. However, it will be HIS AI, and a NEW entity altogether. Our purpose is focused on
preserving the CONCRETE PERSON now (more exactly – his SOUL) in a new body in order
to achieve immortality.
Why is it impossible to directly write the information of the human brain onto a chip?
Because the human brain is constantly changing and neurons permanently change their states.
Imagine you want to record the state of a working computer chip. The chip has millions of
logical elements which change their state millions of times per second. It is obvious that if
you write in series (one after other) the current state of the chip (it is impossible to instantly
write ALL states of the chip‘s elements). To instantly write all neurons one would need to
insert a microelectrode into EVERY neuron, this would destroy the human brain before the
writing was complete.
In the article ―Science, Soul, Parade, and Supreme Mind‖ I offered another method for
the solution of the Main Problem of Immortality.
402 Alexander Bolonkin
5. MODELING OF SOUL FOR A CONCRETE PERSON
As said, straight re-writing of a human mind (human soul) to chips is very complex.
Straight re-writing is not possible in the near future. All scientific works studying the work of
human brains at the present time are useless for the main problem of immortality. They are
also unworkable for the problem of artificial intelligence (AI) in the near term, because the
brain solves problems by way of general estimations. AI solves problems based on more
exact computation and logical data.
To solve the Main Problem of Immortality (MPI) the author offers a method of
―MODELLING SOUL‖ of a concrete person. This method does not require interventions into
the brain of a given person. This method may be applied IMMEDIATELY at the present
time. But an accurate modeling is needed depending on the modeling period.
Before describing this method, let us analyze the human soul and what components are
important for each person and his environment. All information in the human brain (soul)
may be separated in two unequal groups: 1. the Memory (permanent knowledge) about the
person‘s life (all that has been seen, heard, made, felt, people which he has met, his (her)
behaviors, opinions, wishes, dreams, programs of activity, etc.), environment, and 2. Methods
of processing this information, i.e. producing new solutions and new behaviors based on this
knowledge.
The first part (knowledge) is very large. It fills most of the memory and remains
relatively constant (you remember your life, history and you can only fill it by what was in
the past). The second part (methods for deciding, producing solutions based in your
knowledge) is relatively small and constantly changing because of new information, facts and
life experiences.
However, the most important part of a human soul can be written without any problem
now. Industry is producing cheap micro-video recorders as small as a penny, microphones at
grain size, and micro-sensors for vital signs (breathing, palpitation, blood pressure, skin
resistance, perspiration, movement of body parts, etc.). These measurements allow for easy
recording of not only the physical state, but of his moral state (joy, pleasure, grief, trouble,
anxiety, nervousness, etc). For example, lie detectors are able to define not only the state of a
man, but also the truth of his words. Now we can measure and record brain commands and
we can produce small cards with four gigabytes of memory.
It would be easy to attach a video recorder and microphone to a man‘s forehead and then
attach sensors to the body and record all that he sees, hears, speaks, his feelings, reactions,
and activity. And then re-write this information into a personal hard drive (long-term memory
of high capacity storage) at the end of each day. As a result, there is a record of the most
important part our soul – history of life, feelings, environment, behaviors and actions. This
would be more detailed than what is captured by the real man, because the humans forget
many facts, feelings, emotions, and personal interactions. The electronic memory would not
forget anything in the past. It would not forget any person or what they were doing.
But what about the second smaller part of the human soul – producing solutions based on
personal knowledge – perhaps asks the meticulous reader.
This could be restored by using past information from the real man in similar situations.
Moreover, an electronic man could analyze more factors and data in order to throw-out and
exclude actions and emotions that happened under bad conditions. The electronic man
New Concepts, Ideas and Innovations in Aerospace… 403
(named E-being in my previous works) would have a gigantic knowledge base and could in a
matter of second (write to his brain) produce the right answer, much faster than his biological
prototype. That means he would not have the need for the second smaller part of memory.
Considering the environment and friends, the following is an important part of a man‘s
soul: his relationship with parents, children, family, kin, friends, known people, partners and
enemies. This part of his soul will be preserved more completely than even his prototype.
Temporary factors will not influence his relationship with his enemy and friends as would
happen with his former prototype.
There is one problem which may be troubling for some: if we were to record every part
of a person‘s life, how do we keep intimate moments a secret? There are (will be) ways to
protect private information which could be adapted from current usage, for example, the use
of a password (known only by you). Also there may be some moments you choose not to
record information or decide to delete the information from memory.
The offered system may become an excellent tool for defense again lies and false
accusations. You may give the password in one given moment of your life, which proves your
alibi or absence from the accusations.
Some people want to have better memory. Video takes 95% of storage capacity, sound
takes 4% and the rest takes 1%. In usual situations, video can record only separate pictures,
sound only when it appears. This type of recording practice decreases the necessary memory
by tens of times. But every 1.5-2 years chip storage capacity doubles. There are systems
which will compress the information and then may select to record the most important
information (as is done in the human brain). During your life, the possibility to record all
information will be available for all people. This type of recording apparatus will be widely
available and inexpensive. It‘s possible now. The most advanced video recorder or DVD
writes more information than a CD.
Figure 1. Typical devises for writing of main information in human soil.
This solution (recording of human souls) is possible and must be solved quickly. By mass
production (large productions) the apparatus will become inexpensive. The price will drop to
404 Alexander Bolonkin
about $300-1,000. If we work quickly we can begin recording and then more fully save our
souls. The best solution is to begin recording in children when they become aware of ―I‖. But
middle and older people should not delay. Unrecorded life periods may be restored by
pictures, memories, notes, diaries and documents. Soul recovery will only be partial but it‘s
better than nothing.
These records will also be useful in your daily life. You can restore recorded parts of
your life, images of people, relatives, and then analyze and examine your actions for
improvement.
6. DISADVANTAGES OF BIOLOGICAL MEN AND
BIOLOGICAL SOCIETY
People understand Darwin‘s law, ―survival of the fittest‖. For a single person, this law is
the struggle for his/her personal existence (life, well-being, satisfaction of requirements,
pride, etc.). In a completely biological world built on Darwinian law the strongest survives
and reaches his goal. Though they may be intelligent, humans are members of the animal
world. They operate as any other animal in accordance with animal instincts of selfpreservation.
If one is poor, at first he struggles for food (currently half of world‘s population
is starving), dwelling, and better living conditions. When one reaches material well-being, he
may struggle for money, job promotion, reputation, renown, power, attractive women (men),
and so on. Most people consider their activities (include official work) in only one way - what
will I receive from it? Only a small number of people are concerned with the idea of
sacrificing themselves to the well-being (seldom giving up their life) of society at large.
As a result, we see human history as a continuation of wars, dictatorships, and repression
of people by power. Dictators kill all dissidents and opponents. Most people try to
discriminate against opponents and play dirty against their enemy. There are murders, rapes,
violence, robbery, underhand actions, fraud, and lying at all levels of society especially in
lesser developed countries. Each person only cares for himself and his family and does not
care how his actions effect other people or society.
Democratic countries try to cultivate a more civilized society. They create laws, courts,
and have police. Dictator regimes, on the other hand, make only the law they want. I could
give thousands of examples to verify this concept. But hundreds of millions of people are
killed by war, aggressive campaigns, repressions, genocides, and thousands of criminals in
the everyday world are a good illustration of this.
The human brain allows us to reach great success in science and technology. However, as
a biological heritage, struggling for his INDIVIDUAL existence in a bloody, dangerous
world, humans spend much of their resources on mutual extermination of intelligent beings.
Moreover, humans have created ever powerful weapons (for example, nuclear and hydrogen
bombs), which could wipe out humanity. In time, existence may depend on the volition of
one man – perhaps the dictator of a nuclear state.
The second significant drawback to the biological body – is that it spends 99.99% of its
effort and resources simply to support existence. Such as food, lodgings, clothing, sex,
entertainment, relaxation, environment, ecological compatibility. Only a very small part is
New Concepts, Ideas and Innovations in Aerospace… 405
uses for scientific development and new ideas and technology. The reader may see something
wrong here.
States use a parentage of their revenue for research into science and technology. This
percent is used NOT for NEW ideas, but is used to commercialize modern processes All
research is included in the state budget under the name, ―Science and New Technology‖. But
much of this research has little relation to real new scientific progress. Even it the US, states
spend only a small part of the assigned money on new science because state officers do not
understand the research. People, organizations, and companies fight for a piece of the pie.
Geniuses are rare and usually don‘t have the capacity to move forward because they must
promote and pay for new ideas from their own empty packets.
Yet, science and technology has seen success. Most advancement (90%) was made
recently in the 20th century, when governments started to finance a few scientific projects
(compared with the millions of years of human existence). However, our current knowledge
and new technologies are far from what we will eventually have. The first government of an
industrialized country to understand and realize the leading role of new science and
innovation will become powerful.
7. ELECTRONIC SOCIETY
The electronic society will be a society of clever electronic beings (or E-being, as they
named in my articles). Most of the reasons and stimulus which incite men to crime, will be
absent in E-beings. E-beings will not need food, shelter, sex, money, or ecology, which are
the main factors in crime. E-people will not have intense infatuations or be distracted by
behaviors, because they will have vast knowledge about the open electronic society. Their
main work will be in science, innovations, and technologies. They will save their mental
capacity for the production of chips and bodies, scientific devices, experimental equipments,
space ships and space station, etc. They will need a number of robots, which do not need a big
brain. It is likely they will award these robots better minds and memory. It is also likely that
E-man will unite in a common distributed hyper-brain, which will become a sovereign of the
Universe (God).
Nature is infinite and the development of a Super Brain (God) will not be limited. On the
other hand, biological people will have limited mental capabilities. It will be difficult for them
to image and predict the development and activity of Super beings, which we will generate.
Many, especially religious people, object because they say electronic beings will not have
human senses such as love, sympathy, kindness, humanism, altruism, and the capacity to
make mistakes, etc. E-beings are not people. Look back at human history. Human history
shows that kindness played a very small role in human life. All human history is the history
of human vices and human blood: struggle for power, authority, impact, money, riches,
territory, and states. All human history is filled with fraud, underhanded actions, and trickery.
Ordinary people were only playthings, flock of sheep for the tyrants and dictators.
Some people object that with an electronic face humans will loss the joy of sex, alcohol,
narcotics, appreciation of art, beauty, nature, etc. My answer to this question is in my article
―Science, Soul, Heaven, and Supreme Mind‖ (http://Bolonkin.narod.ru). The brief answer is
that electronic humans will enjoy all this in a virtual world or virtual paradise. Time will run
406 Alexander Bolonkin
millions of times faster in the virtual World. E-man will spend a few seconds of real time and
live millions of years in the paradise. He will enjoy any delight imaginable, include sex with
any beautiful women (or handsome men), feel the emotions of any commander, leader,
criminal, or even a dog.
8. LOT (FORTUNE) OF HUMANITY
Biological humanity will be gradually transformed to electronic beings. Old people, when
their biological bodies can not support their brains, will continue their existing in electronic
bodies after death. They will become young, handsome, robust, and. Fertility in biological
men will decrease. Birth-rates are less than death-rates in many civilized countries now (for
example in France). Population growth is mainly supported by emigration from lesser
developed countries. When education levels increase, birth-rates will fall.
For a time, biological and electronic people will exist together. However the distance
between their capabilities will increase very quickly. Electronic people will reproduce
(multiple) by coping, learn instantly, and will not need food or dwellings. They will work full
days in any condition such as in space or on the ocean floor. They will gain new knowledge
in a short time. They will pass this knowledge on to others who do not have enough time. The
distance between biological and artificial intellects will reach a wide margin so that biological
people will not understand anything about new science as monkeys do not understand
multiplication now even after much explanation.
Figure 2. "Actroid ReplieeQ1-expo" at Expo 2005 in Aichi, with co-creator Hiroshi Ishiguro (2000).
New Concepts, Ideas and Innovations in Aerospace… 407
Source: http://world.honda.com/news/2005/c051213_8.html
Figure 2. ASIMO is a humanoid robot created by Honda. Standing at 130 centimeters and weighing 54
kilograms, the robot resembles a small astronaut wearing a backpack and can walk on two feet in a
manner resembling human locomotion at up to 6 km/h. ASIMO was created at Honda's Research and
Development Wako Fundamental Technical Research Center in Japan (2003).
It is obvious, clever people will see that there will be a huge difference between the
mental abilities of biological and electronic entities. They will try to transfer into electronic
form and the ratio between biological and electronic entity will quickly change in electronic
favor. A small number of outliers will continue to live in their biological body in special
enclaves. They will not have industrial power or higher education and will begin to degrade.
Naysayers may promote laws against transferring into an electronic man (as cloning is
forbidden now in some states). However, who would renounce immortality for themselves,
especially while they are young and healthy? One may denounce immorality as blasphemy,
but when your (parents, wife, husband, children) die, especially if you are near death yourself,
one comes to understand that life is extremely important. The possibility to live forever, to
gain knowledge that improves life, will also allow one to become a sovereign force in the
Universe.
REFERENCES
Bolonkin A.A., The twenty-first century: the advent of the non-biological civilization and the
future of the human race, Journal “Kybernetes‖, Vol. 28, No.3, 1999, pp. 325-334, MCB
University Press, 0368-492 (English).
408 Alexander Bolonkin
Bolonkin A.A., Twenty-first century – the beginning of human immortality, Journal
―Kybernetes‖, Vol. 33, No.9/10, 2004, pp. 1535-1542, Emerald Press,
www.emeraldinsight.com/ISSN 0368-492X.htm (English).
Bolonkin A.A., Human Immortality and Electronic Civilization. Electronic book, 1993.
WEB: http://Bolonkin.narod.ru, http://Bolonkin.narod.ru/p101.htm (English),
http://Bolonkin.narod.ru/p100.htm (Russian).
Bolonkin A.A., Science, Soul, Heaven and Supreme Mind, http://Bolonkin.narod.ru. Personal
site: Bolonkin A.A., http://Bolonkin.narod.ru
Bibliography (about the author and discussing his ideas) publication in Russian press and
Internet in 1994 - 2004 (http://www.km.ru, http://pravda.ru, http://n-t.ru, ets. Search:
Bolonkin).
The above Chapter 4 has been translated from a Russian article, ―Proriv v bessmertie‖
(Breakthrough in Immortality) (1999).
Bolonkin A.A., Human Immortality and Electronic Civilization, Lulu, 3-rd Edition, 2007,
(English and Russian), 66 pgs, http://www.lulu.com search ―Bolonkin‖.
APPENDIX 1. SPACE RESEARCH:
ORGANIZING FOR ECONOMICAL EFFICIENCY
ABSTRACT
At present time the USA‘s Federal Government spends big money for an
aviation/space RandD. How to best organize these activity, how to best estimate its utility
and profit (real and potential), how to best increase efficiency, how to best estimate new
ideas and innovations, how to properly fund RandD of new ideas and innovations, and
how to correctly estimate their results - all these macro-problems are important for
successful planning of aviation and space research, new launch and flight systems.
Author considers these major problems and offers many innovations in organization,
estimation, suggests new research efficiency criteria, development, new methods for
assessments of new ideas, innovations in space industry, and new methods in patenting
technology.
The author worked for many years within the USA‘s Federal Government entities
(scientific laboratories of NASA, Air Force, industry), universities and private sector
companies.
Keywords: Organizing scientific research, planning of research, funding research,
funding new ideas (concepts), funding inventions and innovations, estimating research cost,
assessment of research results, research efficiency criteria, innovation in organizing of
scientific RandD.
1.INTRODUCTION
Since beginning of the Twentieth Century, science and technology have held the main
role in human progress. Humanity created more new knowledge more than during many
previous centuries. People researched aerodynamics, flight dynamics and the design of
aircraft. Trained people developed rocket theory and traveled to outer space and the Moon.
Organized research focused on nuclear physics began the exploration of nuclear energy and
the creation of powerful computers, which help in further study of Nature. Astronomy‘s
In this Appendix it is used the report of Dr. A. Johnson accepted as paper AIAA-2006-7224 by Conference
"Space-2006", 19-21 September 2006, San Jose, California, USA (permission by A. Johnson).
410 Alexander Bolonkin
devices allow humans to see and study worlds located millions of the light years beyond
Earth.
The power and influence any modern State in our World is defined by its science,
technology, and industry. The USA is a World leader because, for many years the USA
industry and national government spent more money than any other country to RandD
science-based technical innovations. For example, the USA funds space research more the all
other countries combined. In that way the main scientific advances in space, aviation, and
computers are made in the USA.
If the people of the USA still want to continue to be the World leader, they must continue
this practice and further refine this public and private policy. However, it is possible when the
country has competitors and takes part in a competition struggle. The man on Moon became
possible because the former USSR launched the first satellite (1957) and the USA leaders
understood the USA had temporarily lost World leadership in important field of science and
technology. Only in 1969, after the first manned flight to the Moon, did the USA return to
undoubted leadership in space. That program ended in 1972. However, before collapse (1991)
the USSR launched more satellites than all the rest of the World together, including the USA!
The USA decided to restore this program only when China announced its program of manned
Moon exploration.
The second very important side of scientific RandD is the efficient use of available
funding. The financing of any project is limited everywhere, every time. Unlimited funding is
inconceivable. The right organization of scientific funding and research is a very important
element of scientific progress. That includes: organizing and selection of the most feasible
prospective ideas and innovations for research, selection of a ―can do‖ principal investigator -
scientists who is the author or enthusiast of this idea, right estimation of the project cost,
reached results and perspectives of applications.
All these problems are very complex for investigations. However, there are common
criteria that help to solve these problems of selection and organization and save a lot of
money and achieve practical success in short period of time.
The investigation of these macro-problems is impossible without consideration of current
systems and uncovering (critics) its disadvantages. The author suggests new criteria and new
forms of organizing science funding that were tested/applied in limited cases and which show
a high efficiency. He also offers new criteria for estimation of science results which allows
more evenly to estimate the honesty of finished scientific work reports by specialists and to
separate pseudo-scientific or non-honest works.
For customers, leadership and management is also very important for correct estimation
of the cost of an offered research, a capability of principal investigator, group, or organization
to do this research. Unfortunately, the practice shows mistakes occur very often and they cost
millions of dollars. The author suggests a set of simple rules that allow avoiding the big
mistake and big slips in planning of research works.
The human element is very important in the selection and distribution of limited funding.
In many organization we observe and comment on the situation when large government
money distribution—money shifted from all taxpayers to just one man. As the result he
begins to give money to his friends, to his colleagues or worse - to take bribe. He keeps
elementary information about the activities of his organization secret. The author offers a
method for selections making this practice difficult to initiate or continue, allowing avoidance
of criminality.
New Concepts, Ideas and Innovations in Aerospace… 411
2. SUPPORT OF NEW CONCEPTS
The monetary support of new aviation and space concepts is the basic component of
technical progress. All useful things, which we see around us everyday, were developed from
new concepts, ideas researched in past. What is the situation now? Consider the state of
affairs now.
Science and technology are very complex and have very high level now. The production
of new valid concepts and ideas, and the effort to fully substantiate them, can ONLY be done
nowadays by highly educated people. The USA has hundreds of thousands of conventional
scientists. New concepts and ideas generate only very talented people (genius). They are a
few in a group of thousands of scientists. That requires from them very much time and hard
work. That is not paid work in government or company laboratories. The Government and
private laboratories develop ONLY known concepts and ideas because their purpose is to get
maximum profit in shortest time; that means to produce and substantiate new ideas can only
scientist into his own private time. There are a lot of scientists, but most of them do
conventional researches of well-known ideas and small improvements them, all scientists earn
money. All countries are funding science and research, but they do no usually fund new ideas
or concepts. Rather, they assimilate known new technology, often developed in other
countries. The funding for new concepts and ideas are zero in the World!!
In all countries the composers, writers, artists receive a royalty for performance of their
musical compositions, books, works of Art. Why must scientists gift their hard work on new
concepts, ideas, theories, and equations for computations? It is just if companies used their
method of computation to pay a small ($1000) royalty for author.
3. STUDIES OF INNOVATION
The development of new concept and idea can be presented in 4 stages (figure 1).
Efficiency, E, is possible profit, P, divided by cost, C, of realization.
E = P/C. (1)
The innovation development has 4 stages:
(1) The first stage is discovery of new concepts or idea. That stage includes an
appearance of new idea and INITIAL RESEARCH of its possibilities and main
conditions that are requisite for its practicability, initial proof of reality. A person can
be only author of a new concept or idea if he/she made initial research and showed
that this idea may become a future technical reality. A person who ONLY gave the
idea (point 0 in fig.1) is NOT its author because it is easy to produce a lot of ideas
that are beneath or beyond realization. For example, the fantast Jules Verne (1828-
1905) penned his famous book about the first manned flight to the Moon using a
huge cannon. Is he author of the idea for manned flight to Moon employing a big
412 Alexander Bolonkin
gun? No. Even primitive research shows that a human cannot tolerate the
acceleration that is caused by this method, where the vehicle is a cannonball.
Figure 1. Four Stage innovation development.
The first stage is ONLY theoretical; strong individual and talented enthusiast in own time
without any support because unknown concept or idea cannot be in government or company
plan.
(2) The second stage started after publication or public announcement of the primary
idea during a scientific conference. Other researchers join the investigation of the
new idea and make more detailed researches. Most of this new idea research is
theoretical, and only a small part may be experimental.
(3) The third stage includes the production of appropriate experimental examples.
(4) The fourth stage is actual production of marketable versions of the idea.
We show the development of one innovation (curve 1 in fig.1). However, any concept
exhausts itself and its inherent efficiency possibilities over time. The new concept (idea)
appears which promises even more efficiency (curve 2 in fig.1). Conventionally, in initial
time that has less efficiency then old idea, but in future the innovation efficiency became
significantly more than old idea.
For example, as people use an idea to connect a vehicle to horse. Later they invited a
motor vehicle. Then they developed air vehicle. At present, humanity is developing space
vehicles.
4. GOVERNMENT RELATION
Currently, the most important First Stage is the most difficult situation. No Federal or
reliable private sector funding, no extraneous technical support of any kind. This work can do
ONLY enthusiasts at one's own expense. Funding of the new perspective concept or idea is
needed AFTER its initial theoretical research by a widely system of awards and prizes. For
example, the Director of NIAC, Mr. Cassanova, made a sinecure for his friends from funding
New Concepts, Ideas and Innovations in Aerospace… 413
grants BEFORE theoretical research. Most NIAC works are pseudo-scientific researches (see
below in section NIAC).
Recommendations:
There is only one solution of this macro-problem – the USA‘s Government must install
the series (3 - 5) special national Government prizes (awards about $100K) in every important
scientific field (space, energy, computer, biology, physics, etc.) for new concept scientific
researches that are:
(1) Given ONLY for new concepts and ideas developed by author and published or
presented in scientific conference or Internet (stage 1 in fig.1).
(2) The awards must be given ONLY to individuals.
(3) The competition must be OPEN, advertised widely in public notices. ALL pretenders
and their work and proposals announced BEFORE any awards.
(4) The awarding Committee must be from independent well-known scientists in given
field.
The same awards may be also in stage 2 (developing new concept or idea by non-author
of this idea if the author of idea is awarded; or non-author make significant innovations which
develop or solve problems important for progress this idea). In stage 3 the grants can be given
ONLY for experiment or model.
5. NIAC (NASA INSTITUTE FOR ADVANCED CONCEPTS)
The non-experienced reader objects - there exists NIAC (NASA Institute for Advanced
Concepts) that must support new concepts and ideas in aerospace. The World press wrote—
sometimes--that NIAC Director Mr. Cassanova made from this good idea the sinecure for his
friends, protégés and useful people (http://NASA-NIAC.narod.ru).
Mr. Cassanova invented new method of aggravated theft of Government money: he
awards his friends with millions of USA tax dollar just for promising to make a revolutionary
discovery. In other places awards are given for well-known published scientific works in
OPEN competition. It is impossible that Nobel Prize was given for promising to create epochmaking.
But Mr. Cassanova awarded the theoretical works before they were ever presented to
an established scientific society! As a result, the applicant received money before researching
and present an empty and pseudo-scientific "research"!
Mr. Cassanova (NIAC) announced that every proposal is reviewed by 6 reviewers (3
internal + 3 external reviewers), but he refuses to identify or present these reviews. Why?
The explanations are very simple: NO review panels, NO peer reviewers, NO scientists
who took part in the review process, NO voting, NO scientists who see the proposals!
Everything is just fabricated fiction. There is only just Mr. Cassanova in NIAC who changes
all reviewers, all scientists (in all scientific fields!), all panels, and all debates. Who
distributes un-enumerated millions government (taxpayers) money to friends and insiders.
What kinds of proposals are awarded money supports by Mr. Cassanova? An important
part of the answer to this question can be easily found by the reader at a website: http://NASANIAC.narod.ru
and others.
414 Alexander Bolonkin
Overview: The NIAC spent more 40 millions dollars in 8 years, but they did not really
put forth any really new concepts or ideas! The most NIAC final ―research‖ reports are idle
talk (no scientific results, no pre-production models, no correct scientific report, the final
reports content a lot of scientific mistakes, and so on). For example, the final reports don‘t
have any scientific results: Space Elevator (award about 1 millions dollars), Bio Suite (awards
about 1 millions dollars), Chameleon Suit (award about 1 millions dollars), Weather Control
(awards about 1 millions dollars), Winglee M2P2 MagSail (award about 2 millions dollars),
Cocoon vehicle (work contains only scientific mistakes), anti-matter sail (empty useless nonscientific
7 pages work), and so on (see Final Reports in http://NASA-NIAC.narod.ru).
Now the NIAC is just a private manger for ―friends‖ and has spent 90% of governmentissued
taxpayers money not very effectively, and specifically in fraudulent and criminal ways
(see http://NASA-NIAC.narod.ru).
For example, Mr. Robert Cassanova awarded four times millions of dollars to the
following persons: Howe S., Colozza A., Nock K., Cash W., Dubowsky S. He also awarded
three or four times millions of taxpayer contributions to these persons: Hoffman R. Maise G.,
McCarmack E., Rice E., Slough J. Kammash N., Winglee R., Newman D.
The Science Committee of the organization "Citizens Against Government Waste"
(CAGW) awarded NIAC and Mr. Cassanova the "Pseudo-Nobel Prize-2005" for wasting
millions of taxpayer dollars by pseudo-scientific works (GOTO:
http://www.geocities.com/auditing.science or http://auditing-science.narod.ru).
Recommendations:
The President and Congress of the United States of America, needs to, and must,
thoroughly investigate the NIAC situation and must punish, and remove, NASA and USRA
leaders who allow, and create the abuse and corruption from, and by, NIAC. The Science
Committee of CAGW stands ready to present to a Special Investigation Commission the
documents that confirm the statements presented and outlined in this article.
In this saddening and costly national situation, it is the best decision, to stop the wasteful
and ineffective financing of NIAC and pass their functions to Independent Committee created
from well-known scientists, or NASA can create its own Committee from eminent volunteer
scientists or to pass selected managerial functions to the National Science Academy, or
National Science Foundation and to send awards only to finished scientific works in OPEN
competition, or pass these vital functions to the growing and historically relevant and
important International Space Agency Organization (http://www.international-spaceagency.org
or http://www.isa-hq.net) which would be better suited, and able, to stimulate,
enable, and promote advanced space launch, propulsion, power, orbital, and planetary grant
disbursements, RandD and implementation. This is based on an ever-increasing need for
global cooperation, collaboration, common effort, and universal viewpoint. The International
Space Agency‘s Directives, Charter, Purpose, Goals, and Certificate of Incorporation reflects
this reality far better than the USRA or NIAC directives or charters. The many millions in
Government-dispensed tax monies and private sector money and other relevant resources
would be better used under the management and oversight of the International Space Agency
Organization.
The CAGW Science Committee has available already an offer to NASA for a detailed plan
on how to improve the work of NIAC, making it more open and its product more useful, and
to change the dismal situation when one too-powerful and influential person, exemplified in
New Concepts, Ideas and Innovations in Aerospace… 415
the person of Mr. Cassanova personally distributes tens millions of taxpayer money with no
safe guards or oversight.
This plan includes three conventional conditions:
(1) Independent selection Committee having widely-known E-mail address.
(2) Open competition with publication of all nominated scientific works on Internet,
including assessments made by scientists before any funding awards.
(3) Awarding ONLY MADE scientific works not supported from other sources.
Discussing
The CAGW Science Committee considered, in detail, seven of about two hundred awards
made by Mr. Cassanova (GOTO: http://www.geocities.com/auditing.science or
http://auditing-science.narod.ru). Amazingly, 90% of the ―final reports‖ are just idle talk
giving the impression to readers that there are NO talented scientists in the USA! That means,
obviously, that the system of funding and awarding of scientific works is wrong. Mr.
Cassanova is a university system employee and he evidently tries strenuously to fund his
friends and protégés within his system of work. However, universities take the funded money
and do not pay them over to professors who receive their fixed salary. Often, a professor is
overloaded by lectures, direct work with talented students and ordinary classroom
examinations. Such a person does not have time or the possibility to make serious research
that requires huge efforts and much time. That‘s why he/she wrote the idle talk report,
pseudo-scientific work!
The USA National Research Council (NRC) and ORAU (Oak Ridge Associated
Universities) found the best solution of this problem – one send scientists to government
research centers or laboratories and they works full time 1-2 years into it.
Conclusion
The best way is to withdraw this function and this money from NASA-NIAC-USRA,
pass them to Special Government (or the National Academies, ISA) Committee includes
famous scientists and to award the published works (researches) containing new concepts,
ideas, inventions, and innovations. Make it in an open competition!
The Nobel Committee is not awarding the person who only promised to make notable
research. Why does Mr. Cassanova give out millions of American taxpayer dollars to his
friends without any control and government auditing? Any non-scientist can see that their
―final reports‖ are idle talk, non-scientific works and do not cost the gigantic money which
Mr. Cassanova gives his protégé.
The Scientific Committee of a famous organization, the CAGW (Citizen Against
Government Waste), awarded NIAC and Mr. Cassanova Pseudo-Nobel Prize-2005, 2006
[1-2].
In 2007 the NASA closed the NIAC because NIAC spent more 50 millions of dollars but
not presented any real new comcepts, ideas or innovations in 9 years.
416 Alexander Bolonkin
6. NASA (NATIONAL AERONAUTIC AND
SPACE ADMINISTRATION)
The NASA announced that it invites new concepts and ideas and publicizes the address
where scientists can send their researches and proposals. I personally know excellent
scientists who have sent more than twenty RandD proposals documents to this address:
NASA HEADQUARTERS, Unsolicited Proposal Coordinating Office Attn: Sandy
Russo, proposal coordinator, Code 210.H Goddard Space Flight Center Greenbelt, MD 20771
Sandra.R.Russo@nasa.gov
Some of them included in their letters a US Postal Service green return receipt postal
card. But some months they have not received not only reply from NASA but they cannot
receive their postal card - confirmation about receiving research and proposal. That means -
all NASA appeals about innovations are FICTION. NASA became a gigantic organization
that spends huge taxpayer money and has the lowest scientific efficiency in the World.
Example #1: The former USSR spent money for Space in 3-5 times less then NASA and
had a weak industry, but one was a leader of space research in 1957 - 1969 (before American
flight to Moon) and one launched more satellites up to 1991 (when the USSR collapsed).
Example #2: In 1998 one scientist proposed a means to send to Mars a probe containing
hundreds cheap micro-balloons. Every balloon was to have a micro-camera, other devices and
radio-translator connected to the planet orbiting main Mars satellite. The balloon can sustain
flights for months and transmit detailed close-up Mars pictures. However, the NASA spent
tens millions dollars in non-scientific project of small model of aircraft which can make only
one non-controlled flight of a couple of miles. Why? The reason is simple and apparent - in
2003 it will be 100 years of Wright brother flight and for public propaganda needs NASA
sought a quick propaganda "achievement". Result: NASA spent about 100 millions dollars
but cannot send the model of aircraft.
Real scientists who have in the past and still today cooperate with NASA quietly note the
low skill level of many NASA employees. I know very highly educated (two Ph.D.),
experienced scientist (author more 100 scientific works and tens inventions, who applied in
NASA open position of project manager. The personnel department informed him that he
doesn't have a needed score for possible candidate. He applied in three open NASA positions
of research engineers. The answers were same. He tried to get Government investigation of
this case. Commission ascertained: the NASA took these positions the people having only
B.D., did not have experience, published scientific works, patented inventions.
After collapse of the USSR, the NASA loss of an international rival transformed the
NASA into a monster that wastefully consumed about $15 billions and produced very few
scientific achievements, but a lot of space catastrophes. For example, since 1972, during a
period of 34 years, the NASA has sent no manned flights to the Moon. Only now, following
China‘s announced Program of Moon Exploration, the USA Government understood the
USA gap and requests the NASA to reorganize its Program.
Recommendations:
(1) NASA must be separated into two independent, rival organizations. The funding of
them must depend solely on their progress in Space.
New Concepts, Ideas and Innovations in Aerospace… 417
(2) The leaders of programs and leader-scientists must be selected in OPEN competition
on limit time (time of project). The open competition means that the data of
applicators must be published on the Internet BEFORE selection of them by
scientific Committee. Now everywhere in the USA (in state and government
positions) the open competition of applicants is absolute fiction because of the public
absence of data of any selected candidate (education, experience, number of
publications and awarded patents).
(3) NASA must create the independent Scientific Committee for OPEN consideration
the scientific works and proposals that are presented to NASA, awards for useful
MADE researches and recommends perspective works for subsequent investigation.
NASA can advance funding only research that use special equipment or make a
model. NASA must install the NASA prizes for individual researchers who have
openly offered new concepts and ideas.
7. DARPA (DEFENSE ADVANCED PROJECT AGENCY)
DARPA is special government organization for promotion and development of new
concepts and ideas. I know scientists that sent their proposals to DARPA for consideration.
They received an exceedingly strange answer: "Your proposal no in out plan!" How new
(unknown anybody!) concepts or idea to be in DARPA plan? That is sent for consideration
and including in plan! That means the DARPA is operating out its main purpose - careful
consideration of serious proposals and their financial support. The plan makes not Science
Committee from well-known scientists. That makes bureaucrats according with corporative
interests who spent hundreds millions of dollars for projects which cost in hundreds times
less.
Example. The DARPA decided to produce a micro-craft that allows the soldier to see
what is behind a building, bushes, forest, etc. That is very important for saving the lives of
soldiers in conditions of wartime and policemen during peacetime. The industry produced
micro TV camera (volume is 1 cm3
, weight 3-5 g together with battery), radio control for
small aircraft models (you have seen the children radio control cars).
How will experienced man do it? There are millions of hobby model aircraft constructors
in the USA. They do not know high science. But they can produce many models and
experimentally select from the best. Experienced officer announced a prize ($100 - 200K),
after 6 months make a competition, selected and to get a product ready.
What do DARPA bureaucrats make? They go conventional way, enlisting the usual
universities and the usual scientist-professors. DARPA spent many millions of dollars on
research committed by professors and big-name universities. They received tons of equations
and not a single flight model!
After the reckless waste of $100 millions the DARPA passed this project to Air Force
Laboratories. They continue this wrong innovation method by spending even more millions
of the American taxpayers money. I took part in summary reports of universities. What is
typical situation? The university got a grant (about $100K). They present the report with
equations, model made in Air Force Laboratory. They reported about 8 tests of this model (5
times is successful, 2 times is partially successful, and 1 time unsuccessful). I offered to go
418 Alexander Bolonkin
out from building and repeat test – to reveal what is behind a certain building. They would not
agree. Why? Reason: all testing were not successful, model is not control and cannot do the
needed function (recognizing).
Recommendations: Special Science Committee for consideration of proposals, open
competition and publication of Abstracts of all proposals.
8. NSF (NATIONAL SCIENCE FOUNDATION) AND GOVERNMENT
RESEARCH LABORATORIES
All problems of DARPA have place in NSF and Government Research Laboratories. See
Recommendation above.
9. SBIR - SMALL BUSINESS INNOVATION RESEARCH
All problems above are same for SBIR. The SBIR considers practically only proposals
corresponding plan, topics of given department. Idea of SBIR is funding innovations of small
business (group, individuals). But its small business is definition is an organization having
500 employees! That allows the universities and big companies separated their department
and presented it as "small business". We have a similar situation with NIAC - employees have
salary and not interested in given innovation, hard works.
Common note: Most universities, small business and proposed work project initiators are
interested ONLY in getting money grants. They do not have need scientists (especially
enthusiasts), needed experience in given field, needed equipments. In most cases, the grants
are given on the quiet. It is essential to have coattails. As the result, the customer—the
American taxpayer—receives empty works, pseudo-scientific research.
Example.
I want to give one example of relation of noted organizations to revolutionary
innovations.
I personally know one Moscow, Russia university professor. He is a well-known
specialist in structural strength, having many scientific works and books. He invented a new
location of stringers on thin casing which increases a shell‘s stability by 2 - 3 times (that
means a decreasing weight of aircraft, missile, ships structure of about 20 - 30% - surely a
revolution in aviation, rockets, ships). He TESTED his innovations in Moscow and received
excellent results. He arrived in the USA and began to offer his innovation to NASA, DARPA,
Air Force, Department of Defense, NAVY, commercial and military aviation companies. He
did not ask immediately for a research grant, he merely asked only to test conventional
structures and his stronger panels and make sure of his findings. He spent some years seeking
such help. Everywhere, he doesn't receive answers, or received empty formatted replies, or
answer - his innovation absents in plan.
That means: all noted bureaucratic organizations retard progress by the USA.
10. PUBLICATIONS
There are well-known organizations such as the American Institute of Aeronautics and
Astronautics. One makes a big work, organizes aerospace conferences and publishes a series
New Concepts, Ideas and Innovations in Aerospace… 419
of aerospace journals. But it doesn't have support from government and NASA and it became
a strictly commercial organization. For example, the cost of participation in AIAA
conferences is very high. That means only employees of government and big organizations
can take part in scientific forums. But they show only conventional RandD plans. The new
revolutionary ideas and researches are made by talented individuals, enthusiasts in their free
time. They can make a revolutionary research, but they do not have a lot of money (some
thousands of dollars) for payment of trip, hotel and conference fee. Literally, the USA losses
these revolutionary researches.
Editors of AIAA journals do not get salary for their arduous efforts. That means they
want to see their name in every copy of journal, but they do not want to work as editor. They
pass article to reviewer and pass review to author. That function can be done via computer.
Some of them converted the journal in private edition for their friends and protégé. For
example, all 20 revolutionary researches published in recent comprehensive book "NonRocket
Space Launch and Flight", Elsevier, London, 2006, offered for publication in AIAA
"Journal of Power and Propulsion" (JPP), but all were rejected by editor-in-chief Vigor
Yang as researches are written non-American style and having poor English. What is
"American style" he cannot explain, English the readers can see the book and decide: is it
important reason in refusal in revolutionary innovations? For some last years the "JPP" have
not published any revolutionary ideas, but published many articles having principle scientific
mistakes. The same situation with AIAA "Journal of Spacecraft and Rockets" (Editor-inChief
Vincent Zoby).
It is bad, that the USA has only single journal about power and propulsion system or
spacecraft and American authors must publish new ideas and researches in abroad journals.
It is bad that commercial publishing houses do not want to publish scientific literature,
because it is not profitable. As a result, the scientific literature (and text-books) are very
expensive and prohibitive not only for students, but for scientists.
It is bad that no free scientific Internet library and AIAA requests about $1000 for every
publication in journal and sells every scientific article for $10.
Recommendations:
(1) The USA must have minimum two rival journals in every scientific field. Every
journal must have Appeal Commission where author can complain if he/she does not
agree with editor clearly stated reasons for article rejection.
(2) Every National Conference must have small fund for supporting the individuals
presented revolutionary research and give them possibility to address a meeting.
(3) Government and NASA must support with appropriate funding the points 1-2 above
(scientific journal and scientific conferences), the AIAA (and all big old Scientific
Societies), the scientific publishing houses, the free scientific Internet library.
(4) The AIAA (and all big old Scientific Societies) must free publish in Internet all
manuscripts presented in AIAA Scientific Conferences.
The Government, country loss more on obstacles which exists for appearing and
applications new ideas, the most of them produced by individual talented researchers.
420 Alexander Bolonkin
11. PATENTING
The USA Constitution proclaims a support of science and patenting. Unfortunately, the
USA PTO (Patent and Trademark Office) had become a powerful means to extract money
from inventive people. The Payment for PTO equals some thousands dollars and prohibitive
for individuals. The patenting approval process continues for at least 1-2 years. If the inventor
complains, the PTO can sabotage all your inventions. I personally know of a case when an
inventor paid for invention but PTO did not give a patent. The PTO creates a lot of Rules that
permit the pumping of money from people and that allows the sabotaging of the patenting
process.
Recommendations:
(1) Now the PTO has rates for big Companies and for small Business. It must be a
special rate for individuals and FULL payment (application, patenting, and
maintenance) must be not more $100 for them.
(2) It must be category "important patents for Department of Defense and the USA". If
Special Committee recognized a patent application as necessary (important) for
Department of Defense or the USA, the applicant has a right to a free patenting (he
received only author certificate, the Government get all patent rights), all USA
organizations or companies can use this patent but they must pay its author 1% and
PTO 1% from cost of product used under this patent.
(3) All income received by PTO must be used for support of individual inventors.
12. FINAL RECOMMENDATIONS
Current system organization and funding of science researches is not efficiency
especially for NIAC, NASA, DARPA, DoD, AF, SBIR, NSF, PTO. They need
reorganization. Main components of reformation must be the following:
(1) The unwise and wasteful practice of advance funding of primary theoretical
researches must be stopped and changed to OPEN competitions in any given field
and in given topics. NASA must stop funding NIAC and must demand from USRA
to return money held by Mr. Casanova‘s group.
(2) Government must install 3-5 annual Government Prizes (about $100K) in every
important field of science (space, aviation, computer, physics, biology, energy, etc.)
for important THEORETICAL achievements made by individuals.
(3) The company used new method of computation must pay small ($1000) royalties to
authors from every use.
(4) NASA must be divided into two independent rival organizations.
(5) The main method funding of research must be not funding Universities but it must be
the work of University scientists done during 1-3 years as Fellow researchers in big
Government laboratories.
New Concepts, Ideas and Innovations in Aerospace… 421
(6) NASA, DARPA, Government laboratories must engage a head and main specialists
of every project in OPEN concourses, preferably the authors of project (proposal)
and scientists made main contributions in the project idea or concepts.
(7) The Government must support main scientific journals, publishing houses, free
Internet scientific libraries; individual scientists presented an important researches to
scientific national conferences.
(8) Government must make special small rate (<$100) for individual inventors, free
patenting of important for DoD and the USA inventions and to use all PTO profit for
support individual inventors important for DoD and the USA.
REFERENSES
1. GOTO: http://NASA-NIAC.narod.ru.
2. GOTO: http://auditing-science.narod.ru or http://www.geocities.com/auditing.science.
APPENDIX 2
ABSTRACT
Here there are values useful for calculations and estimations of aerospace and
technical projects.
1. SYSTEM OF MECHANICAL AND ELECTRICAL UNITS
The following table contains the delivered metric mechanical and the electromagnetic SI
units that have been introduced in this text, expressed in terms of the fundamental units meter,
kilogram, second, and ampere. From these expressions the dimensions of the physical
quantities involved can be readily determined.
Length 1 meter = 1 m Force 1 newton = 1 N = 1 kg·m/s2
Mass 1 kilogram = 1 kg Pressure 1 N/m2 = 1 kg/m.
s
2
Time 1 second = 1 s Energy 1 joule = 1 J =1 N/m = 1 kg.m
2
/s2
Electric
current 1 ampere = 1 A Power 1 watt = 1 W =1 J/s = 1 kg.m
2
/s
3
Rotational inertia 1 kilogram.meter2
= 1 kg.m
2
Torque 1 meter.
newton = 1 kg.m
2
/s2
Electric charge 1 coulomb = 1 C = 1 A.
s
Electric intensity 1 N/C = 1 V/m = 1 kg.m/s3.A
Electric potential 1 volt = 1 V = 1 J/C = 1 kg.m
2
/s3.A
Electric resistance 1 ohm =1 Ω =1 V/A = 1 kg.m
2
/s3.A
2
Capacitance 1 farad = 1 F =1 C/V = 1 C2/J = 1 s4.A
2
/kg.m
2
Inductance 1 henry = 1 H =1 J/A2 = 1 Ω.
s = 1 kg.m
2
/s2.A
2
Magnetic flux 1 webwer = 1 Wb = 1 J/A = 1 V.s = 1 kg.m
2
/s2.A
Magnetic intensity 1 tesla = 1 Wb/m2 =1 V.s/m2 =1 kg/s2.A
Reluctance 1 ampera-turn/weber = 1 A/Wb =1 s2.A
2
/kg.m
2
Magnetizing force 1 ampere-turn/meter = 1 A/m
424 Alexander Bolonkin
Kelvin is fundamental unit of temperature
Candela is fundamental power-like unit of photometry
FUNDAMENTAL PHYSICAL CONSTANTS
Standard gravitational acceleration 9.806 65 m/s2
Standard atmosphere (atm) 101 325 N/m2
Thermochemical kilocalorie 4184 J
Speed of light in vacuum (c) 2.997 935×108 m/s
Electronic charge (e) 1.60210×10–19 C
Avogadro constant (NA) 6.0225×1026/kmol
Faraday constant (F) 9.6487×107 C/kmol
Universal gas constant (R) 8314 J/kmol
Gravitational constant (G) 6.67×10–11 N
.m
2
/kg2
Boltzmann constant (k) 1.3895×10–23 J/K
Stefan-Boltzmann Constant (σ) 5.670×10–8 W/K4.
m
2
Rest energy of one atomic mass unit 931.48 MeV
Electron-volt (eV) 1.60210×10–19 J
Rest masses of particles
(u) (kg) (MeV)
Electron 5.485 97×10–4
9.1091×10–31
0.511 006
Proton 1.002 2766 1.672 52×10–27 938.26
α-particles 4.001 553 6.6441×10–27 3727.3
Astronomical Data
Density of gases at normal pressure and temperature 0 oC in kg/m3
Air 1.293
Hydrogen 0.08988
Helium 0.1785
New Concepts, Ideas and Innovations in Aerospace… 425
Parameters of Earth atmosphere (relative density and temperature)
Specific impulse of liquid fuel (nozzle 100:0.1, seconds):
Oxygen – kerosene 372
Oxygen – hydrogen 463
Specific impulse of solid fuel (nozzle 40:0.1, seconds): 228–341.
Heat of combustion (MJ/kg):
Benzene 44 Mazut 30–41 Natural gases 42–47 Firewood 30
Diesel fuel 43 Spirit 27.2 Hydrogen 120 Peat 8 –11
Kerosene 43 Bituminous coal 21–24 Acetylene 48 gunpowder 3
GENERAL REFERENCES
(Part of these works are in http://Bolonkin.narod.ru/p65.htm and in http://arxiv.org
search: "Bolonkin")
[1] Bolonkin A.A., (1958a). Design of Hydro-Aircraft with Underwater Wing. Report of
Aircraft State Construction Bureau named Antonov, Kiev, Ukraine, 1959 (in Russian),
120 p.
[2] Bolonkin A.A., (1959a). Investigation of Aircraft AN-12 in Take-off. Report of Aircraft
State Construction Bureau named Antonov, Kiev, Ukraine, 1959 (in Russian), 60 p.
[3] Bolonkin A.A., (1959b). Research of Optimal Parameters of VTOL Aircraft, Report of
Aircraft State Construction Bureau named Antonov, Kiev, 1959 (in Russian), Part 1 40
p., part 2 35 p.
[4] Bolonkin A.A., (1959c). Research of Optimal Parameters of High Altitude Aircraft.
Report of Aircraft State Construction Bureau named Antonov, Kiev, Ukraine, 1959 (in
Russian), 60 p.
[5] Bolonkin A.A., (1959d). Computation of High Thrust Aircraft with unsteady polar.
Report of Aircraft State Construction Bureau named Antonov, Kiev, Ukraine, 1959 (in
Russian), 50 p.
[6] Bolonkin A.A., (1960a). Method of Estimation the Control of Aircraft Interface.
Presiding of Kiev High Engineering Aviation Military School (KVIAVU), Kiev,
Ukraine, Issue #72, 1960.
[7] Bolonkin A.A., (1962a), Theory of Flight Models, Moscow, Association of Army, Air
Force, and NAVY, 328p. 1962, (in Russian).
[8] Bolonkin A.A., (1964a). Optimization of parameters of variation problems (Ukrainian.
Russian and English summaries). Dopoviti Akad. Nauk Ukrain. RSR, 1964, #5, p. 580-
582. Math.Rev. #6352.
[9] Bolonkin A.A., (1964b)The calculus of variations and a functional equation of Bellman,
and an interpretation of Langrange‘s undetermined multipliers. (Ukrainian. Russian and
English summaries). Dopovidi Akad. Nauk Ukrain., RSR 1964, #10, p. 1290-1293. M.R.
#5136.
[10] Bolonkin A.A., (1964c). The extension principle and the Jacobi condition of the
variation calculus. (Ukrainian. Russian and English summaries). Dopovidi Akad. Nauk
Ukrain. RSR 1964. #7. p. 849-853. M.R. #5117.
428 Alexander Bolonkin
[11] Bolonkin, A.A., (1965a), ―Theory of Flight Vehicles with Control Radial Force‖.
Collection Researches of Flight Dynamics, Mashinostroenie Publisher, Moscow, pp.
79–118, 1965, (in Russian). Intern.Aerospace Abstract A66-23338# (Eng).
[12] Bolonkin A.A., (1965b), Investigation of the Take off Dynamics of a VTOL Aircraft.
Collection Researches of Flight Dynamics. Moscow, Mashinostroenie Publisher, 1965,
pp. 119-147 ( in Russian). International Aerospace Abstract A66-23339# (English).
[13] Bolonkin A.A., (1965c), Optimization of Trajectories of Multistage Rockets. Collection
Researches of Flight Dynamics. Moscow, 1965, p. 20-78 (in Russian). International
Aerospace Abstract A66-23337# (English).
[14] Bolonkin A.A., (1965d). A method for the solution of optimal problems (Russian).
Collection Complex Systems Control, pp.34-67. Naukova Dumka, Kiev, 1965. M.R.
#5535.
[15] Bolonkin A.A., (1965e). Special, Sliding, and Impulse Regimes in Problems of Flight
Dynamics (Russian). Collection Complex Systems Control, pp.68-90. Naukova Dumka,
Kiev, 1965. M.R. #5535.
[16] Bolonkin A.A., (1966a). Boundary-value problems of Optimal Control. Military
Aviation Engeenering Academy (VVIA) named Zhukovskii, Issue #1131, 1966, p. 103-
128. (Russian).
[17] Bolonkin A.A., (1967a). Special extreme, Report presented to Symposium of Applied
Mathematics, Gorkii, USSR, 1967. (Russian).
[18] Bolonkin A.A., (1968a). Impulse solution in control problems. (Russian). Izv. Sibirsk.
Otdel. Akad. Nayk USSR, 1968, No. 13, p. 63-68. M.R. 7568. (Russian).
[19] Bolonkin A.A., (1968b). Solution of Problem the Linear Optimal Control with one
Control, Journal "Prikladnaya Mechanica", Vol. 4, #4, 1968, p.111-121. (Russian).
[20] Bolonkin A.A., (1969a). Solution of discrete problems of optimal control on the basis
of a general minimum principle (Russian. English summary). Vycisl. Prikl. Mat. (Kiev)
Vyp. 7 (1969), 121-132. Mathematical Review 771.
[21] Bolonkin A.A., (1969b), Special extreme in optimal control. Akademia Nauk USSR,
Izvestiya. Tekhnicheskaya Kibernetika, No 2, Mar-Apr.,1969, p.187-198. See also
English translation in Engineering Cybernetics, # 2, Mar- Apr.1969, p.170-183,
(English).
[22] Bolonkin A.A., (1970a). A certain method of solving optimal problems. Izv. Sibirsk.
Otdel. Akad. Nauk SSSR. 1970, no.8, p. 86-92. M.R. #6163.
[23] Bolonkin A.A., (1970b). A certain approach to the solution of optimal problems.
(Russian. English summary). Vycisl. Prikl. Mat. (Kiev). Vyp. 12 (1970), p. 123-133.
M.R. #7940.
[24] Bolonkin A.A., (1971a), Solution Methods for boundary-value problems of Optimal
Control Theory. Translated from Prikladnaya Mekhanika, Vol. 7, No 6, 1971, p. 639-
650, (in English).
[25] Bolonkin A.A., (1971b). Solution of Optimal Problems. Collection "Mathematical
Problems of Production Control", Moscow State University (MGU), Issue #3, 1971, p.
55-67.
[26] Bolonkin, A.A., (1972a), New Methods of Optimization and their Applications,
Moscow Highest Technology University named Bauman, 1972, p.220 (in Russian).
[27] Bolonkin, A.A., (1982a), Installation for Open Electrostatic Field, Russian patent
application #3467270/21 116676, 9 July, 1982 (in Russian), Russian PTO.
New Concepts, Ideas and Innovations in Aerospace… 429
[28] Bolonkin, A.A., (1982b), Radioisotope Propulsion. Russian patent application
#3467762/25 116952, 9 July 1982 (in Russian), Russian PTO.
[29] Bolonkin, A.A., (1982c), Radioisotope Electric Generator. Russian patent application
#3469511/25 116927. 9 July 1982 (in Russian), Russian PTO.
[30] Bolonkin, A.A., (1983a), Space Propulsion Using Solar Wing and Installation for It,
Russian patent application #3635955/23 126453, 19 August, 1983 (in Russian), Russian
PTO.
[31] Bolonkin, A.A., (1983b), Getting of Electric Energy from Space and Installation for It,
Russian patent application #3638699/25 126303, 19 August, 1983 (in Russian), Russian
PTO.
[32] Bolonkin, A.A., (1983c), Protection from Charged Particles in Space and Installation
for It, Russian patent application #3644168 136270, 23 September 1983, (in Russian),
Russian PTO.
[33] Bolonkin, A. A., (1983d), Method of Transformation of Plasma Energy in Electric
Current and Installation for It. Russian patent application #3647344 136681 of 27 July
1983 (in Russian), Russian PTO.
[34] Bolonkin, A. A., (1983e), Method of Propulsion using Radioisotope Energy and
Installation for It. of Plasma Energy in Electric Current and Installation for it. Russian
patent application #3601164/25 086973 of 6 June, 1983 (in Russian), Russian PTO.
[35] Bolonkin, A. A.,(1983f), Transformation of Energy of Rarefaction Plasma in Electric
Current and Installation for it. Russian patent application #3663911/25 159775, 23
November 1983 (in Russian), Russian PTO.
[36] Bolonkin, A. A., (1983g), Method of a Keeping of a Neutral Plasma and Installation
for it. Russian patent application #3600272/25 086993, 6 June 1983 (in Russian),
Russian PTO.
[37] Bolonkin, A.A.,(1983h), Radioisotope Electric Generator. Russian patent application
#3620051/25 108943, 13 July 1983 (in Russian), Russian PTO.
[38] Bolonkin, A.A., (1983i), Method of Energy Transformation of Radioisotope Matter in
Electricity and Installation for it. Russian patent application #3647343/25 136692, 27
July 1983 (in Russian), Russian PTO.
[39] Bolonkin, A.A., (1983j). Method of stretching of thin film. Russian patent application
#3646689/10 138085, 28 September 1983 (in Russian), Russian PTO.
[40] Bolonkin A.A., (1984a). Method Solution of Optimal Problem, Collection "Research of
Computer and Control System", Irkutsk, USSR, 1984, pp.94-98. (in Russian).
[41] Bolonkin A.A., (1987a). Method of Deformation of Extreme. Collection "Methods and
Programs of Optimal Problems in Networks", Irkutsk State University and West
Siberian Technological Institute, 1987, (in Russian).
[42] Bolonkin A.A., (1987b). Method for Solution of Optimal Problems having equalities
and non-equalities limitations. Collection "Methods and Programs of Optimal Problems
in Networks", Irkutsk State University and West Siberian Technological Institute, 1987,
(in Russian).
[43] Bolonkin A.A., (1988a). Application of the Deformation Method to Optimization
Problems on any Set" (in Russian), Collection "Design of Micro-processors", Irkutsk
(USSR), 1988 9 p.
[44] Bolonkin A.A., (1988b). Deformation Method in Control Problems" (in Russian),
Collection "Design of Micro-processors", Irkutsk (USSR), 1988 10 p.
430 Alexander Bolonkin
[45] Bolonkin, A.A., (1990a). ―Aviation, Motor and Space Designs‖, Collection Emerging
Technology in the Soviet Union, 1990, Delphic Ass., Inc., pp.32–80 (English).
[46] Bolonkin, A.A., (1991a), The Development of Soviet Rocket Engines, 1991, Delphic
Ass.Inc.,122 p. Washington, (in English).
[47] Bolonkin, A.A., (1991b), New Approach to Finding a Global Optimum. New
American’s Collected Scientific Reports. Vol. 1, 1991, The Bnai Zion Scientists
Division., New York.
[48] Bolonkin, A.A., (1992a), ―A Space Motor Using Solar Wind Energy (Magnetic Particle
Sail)‖. The World Space Congress, Washington, DC, USA, 28 Aug. – 5 Sept., 1992,
IAF-0615.
[49] Bolonkin, A.A., (1992b), ―Space Electric Generator, run by Solar Wing‖. The World
Space Congress, Washington, DC, USA, 28 Aug. –5 Sept. 1992, IAF-92-0604.
[50] Bolonkin, A.A., (1992c), ―Simple Space Nuclear Reactor Motors and Electric
Generators Running on Radioactive Substances‖, The World Space Congress,
Washington, DC, USA, 28 Aug. – 5 Sept., 1992, IAF-92-0573.
[51] Bolonkin A.A., The Twenty - First Century: The advent of the non-biological
civilization. http://Bolonkin.narod.ru .
[52] Bolonkin, A.A. (1994a), ―The Simplest Space Electric Generator and Motor with
Control Energy and Thrust‖, 45th International Astronautical Congress, Jerusalem,
Israel, 9–14 Oct., 1994, IAF-94-R.1.368.
[53] Bolonkin A.A., Khot N., (1994b), Optimal Structural and Control Design. 45th
International Actronautical Congress. Jerusalem, Israel. October 9-14, 1994, IAF-94-
I.4.206.
[54] Bolonkin A.A., (1994c), Method for Finding a Global Minimum,
AIAA/NASA/USAF/SSMO Symposium on Multi-disciplinary Analysis and
Optimization, Panama City, Florida, USA, Sept. 7-9, 1994.
[55] Bolonkin A.A., Khot N., (1995a), Design and Optimal Control in Smart Structures.
Conference “Mathematics and Control in Smart Structures‖, 26 Feb.-3 March 1995,
San Diego, CA, USA.
[56] Bolonkin A.A., Khot N., (1995b), Optimum Structural Vibration Control with Bounds
on Control Forces, 1995 ASME Design Technical Conference, 15th Biennial
Conference on Vibration and Noise, September 17-21,1995, Boston, MA, USA.
[57] Bolonkin A.A., (1995c), Twenty - First Century - the beginning of human immortality.
http://Bolonkin.narod.ru .
[58] Bolonkin A.A., Khot N., (1996a), Optimal Bounded Control Design for Vibration
Suppression. Acta Astronautics, Vol.38, No. 10, pp803-813, 1996.
[59] Bolonkin A.A., Khot N., (1996b), Minimum Weight of Control Devices with Bounded
LQG Control. The World Space Congress -96, June 1-6, 1996, Albuquerque, MN,
USA.
[60] Bolonkin A.A., Khot N., (1996c), Design of Smart Structures with Bounded Controls,
Smart Structures and Materials, Feb. 25-29,1996,San-Diego, CA.
[61] Bolonkin A.A., Khot N., (1997a), Design of Structure control System using Bounded
LQG, Eng.Opt., 1997, Vol. 29, pp. 347-358.
[62] Bolonkin A.A., (1997b). Eccentric internal combustion engine. Patent application US
PTO 08/892,665 of 07/14/97.
New Concepts, Ideas and Innovations in Aerospace… 431
[63] Bolonkin A.A., (1998a). Inflatable flight vehicles. Patent application US PTO
09/271,700 of 1/26/98.
[64] Bolonkin A.A., (1998b). Inflatable flight vehicles. Patent application US PTO
09/271,700 of 1/26/98.
[65] Bolonkin A.A., (1999a). Method of space launch and hypersonic launch system. Patent
application US PTO 09/344,235 of 6/25/99.
[66] Bolonkin, A.A. (1999b), A High Efficiency Fuselage propeller (―Fusefan‖) for
Subsonic Aircraft, !999 World Aviation Congress, AIAA, #1999-01-5569.
[67] Bolonkin A.A., Gilyard G.B., (1999c), Estimated Benefits of Variable-Geometry Wing
Camber Control for Transport Aircraft. NASA Center for AeroSpace Information
(CASI), NASA/TM-1999-206586; H-2368; NAS 1.15:206586 , 19991001; October 1999
[68] Bolonkin A.A., (1999d). The twenty-first century: the advent of the non-biological
civilization and the future of the human race, Journal ―Kybernetes‖, Vol. 28, No.3,
1999, pp. 325-334, MCB University Press, 0368-492 (English).
[69] Bolonkin A.A., (1999e). Science, Soul, Heaven and Supreme Mind,
http://Bolonkin.narod.ru (Russian, English).
[70] Bolonkin A.A., (1999d). Breakthrough in Immortality. http://Bolonkin.narod.ru
(Russian, English).
[71] Bolonkin A.A., (1999d). Human Immortality and Electronic Civilization. Electronic
book, 1999. WEB: http://Bolonkin.narod.ru, http://Bolonkin.narod.ru/p101.htm
(English), http://Bolonkin.narod.ru/p100.htm (Russian).
[72] Bolonkin A.A., Gilyard G.B., (2000a), Optimal Pitch Thrust-Vector Angle and Benefits
for all Flight Regimes, NASA Center for AeroSpace Information (CASI), NASA/TM2000-209021;
NAS 1.15:209021; H-2402 , 20000301; March 2000.
[73] Bolonkin A.A., (2001a). Method and Installation for Space Trip. Patent application US
PTO 09/789,959 of 2/23/01.
[74] Bolonkin A.A., (2001b). Method and Installation for Space Launch. Patent application
US PTO 09/873,985 of 6/04/01.
[75] Bolonkin A.A., (2001c). "Method Transportation of Vehicles and Installations for It".
Patent application US PTO 09/893,060 of 6/28/01. Patent US 6,434,143 B1 of
12/17/02.
[76] Bolonkin A.A., (2001d). Method and Installation for getting of Energy. Patent
application US PTO 09/945,497 of 9/06/01.
[77] A.A. Bolonkin, (2001e). "Method for Gas and Payload Transportation at Long
Distance and Installations for It", Patent Application USPTO # 09/978,507 of 10/18/01.
[78] Bolonkin A.A., (2001f). Cable Launcher. Patent application US PTO 09/974,670 of
10/11/01.
[79] Bolonkin, A.A., (2002a), ―Non-Rocket Space Rope Launcher for People‖, IAC-02-
V.P.06, 53rd International Astronautical Congress, The World Space Congress – 2002,
10–19 Oct 2002, Houston, Texas, USA.
[80] Bolonkin, A.A,(2002b), ―Non-Rocket Missile Rope Launcher‖, IAC-02-IAA.S.P.14,
53rd International Astronautical Congress, The World Space Congress – 2002, 10–19
Oct 2002, Houston, Texas, USA.
[81] Bolonkin, A.A.,(2002c), ―Inexpensive Cable Space Launcher of High Capability‖, IAC02-V.P.07,
53rd International Astronautical Congress, The World Space Congress –
2002, 10–19 Oct 2002, Houston, Texas, USA.
432 Alexander Bolonkin
[82] Bolonkin, A.A.,(2002d), ―Hypersonic Launch System of Capability up 500 tons per day
and Delivery Cost $1 per Lb‖. IAC-02-S.P.15, 53rd International Astronautical
Congress, The World Space Congress – 2002, 10–19 Oct 2002, Houston, Texas, USA.
[83] Bolonkin, A.A.,(2002e), ―Employment Asteroids for Movement of Space Ship and
Probes‖. IAC-02-S.6.04, 53rd International Astronautical Congress, The World Space
Congress – 2002, 10–19 Oct 2002, Houston, Texas, USA.
[84] Bolonkin, A.A., (2002f), ―Optimal Inflatable Space Towers of High Height‖. COSPAR02
C1.1-0035-02, 34th Scientific Assembly of the Committee on Space Research
(COSPAR), The World Space Congress – 2002, 10–19 Oct 2002, Houston, Texas,
USA.
[85] Bolonkin, A.A., (2002g), ―Non-Rocket Earth-Moon Transport System‖, COSPAR-02
B0.3-F3.3-0032-02, 02-A-02226, 34th Scientific Assembly of the Committee on Space
Research (COSPAR), The World Space Congress – 2002, 10–19 Oct 2002, Houston,
Texas, USA.
[86] Bolonkin, A. A.,(2002h) ―Non-Rocket Earth-Mars Transport System‖, COSPAR-02
B0.4-C3.4-0036-02, 34th Scientific Assembly of the Committee on Space Research
(COSPAR), The World Space Congress – 2002, 10–19 Oct 2002, Houston, Texas,
USA.
[87] Bolonkin, A.A.,(2002i). ―Transport System for Delivery Tourists at Altitude 140 km‖.
IAC-02-IAA.1.3.03, 53rd International Astronautical Congress, The World Space
Congress – 2002, 10-19 Oct. 2002, Houston, Texas, USA.
[88] Bolonkin, A.A., (2002j), ‖Hypersonic Gas-Rocket Launch System.‖ AIAA-2002-3927,
38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 7–10 July
2002. Indianapolis, IN, USA.
[89] Bolonkin A.A., Cloutier D., (2002k). Search, Observation, and Attack Problems,
Technical Report AFRL-MN-EG-TR-2003-1717, 21p. 2002.
[90] Bolonkin, A.A., (2003a), ―Air Cable Transport‖, Journal of Aircraft, Vol. 40, No. 2,
March–April 2003.
[91] Bolonkin, A.A., (2003b),―Optimal Inflatable Space Towers with 3-100 km Height‖,
JBIS, Vol. 56, No 3/4, pp. 87–97, 2003.
[92] Bolonkin, A.A.,(2003c), ―Asteroids as Propulsion Systems of Space Ships‖, JBIS, Vol.
56, No 3/4, pp. 97–107, 2003.
[93] Bolonkin A.A., (2003d), ―Non-Rocket Transportation System for Space Travel‖, JBIS,
Vol. 56, No 7/8, pp. 231–249, 2003.
[94] Bolonkin A.A., (2003e), ―Hypersonic Space Launcher of High Capability‖, Actual
problems of aviation and aerospace systems, Kazan, No. 1(15), Vol. 8, 2003, pp. 45–
58. Kazan Aviation Institute.
[95] Bolonkin A.A., (2003f), ―Centrifugal Keeper for Space Stations and Satellites‖, JBIS,
Vol. 56, No 9/10, pp. 314–327, 2003.
[96] Bolonkin A.A., (2003g), ―Non-Rocket Earth-Moon Transport System‖, Advances in
Space Research, Vol. 31/11, pp. 2485–2490, 2003, Elsevier. London.
[97] Bolonkin A.A., (2003h), ―Earth Accelerator for Space Ships and Missiles‖. JBIS, Vol.
56, No. 11/12, 2003, pp. 394–404.
[98] Bolonkin A.A., (2003i), ―Air Cable Transport and Bridges‖, TN 7567, International Air
and Space Symposium – The Next 100 Years, 14–17 July 2003, Dayton, Ohio, USA.
New Concepts, Ideas and Innovations in Aerospace… 433
[99] Bolonkin, A.A., (2003j), ―Air Cable Transport System‖, Journal of Aircraft, Vol. 40,
No. 2, March-April 2003, pp. 265-269.
[100] Bolonkin A.A., Sierakowski R., (2003k). Design of Optimal Regulators. The
manuscript is accepted as paper AIAA-2003-6638 by 2nd AIAA ―Unmanned
Unlimited― Systems, Technologies, and Operations- Aerospace, Land, and See
Conference and Workshop and Exhibit, San Diego, California, USA, 15-18 Sep 2003.
http://arxiv.org , search "Bolonkin".
[101] Bolonkin A.A., Murphy R., (2003-l). Geometry-Based Feasibility Constraints for
Single Pursuer Multiple Evader Problems, 2nd AIAA ―Unmanned Unlimited‖ Systems,
Technologies, and Operations – Aerospace, Land, and sea Conference and Workshop
and Exhibit, San Diego, California, 15-18 Sep 2003, AIAA-2003-6638.
[102] Bolonkin A.A.,(2004a), ―Kinetic Space Towers and Launchers ‗, JBIS, Vol. 57, No 1/2,
pp. 33–39, 2004.
[103] Bolonkin A.A.,(2004b), ―Optimal trajectory of air vehicles‖, Aircraft Engineering and
Space Technology, Vol. 76, No. 2, 2004, pp. 193–214.
[104] Bolonkin A.A., (2004c), ―Long Distance Transfer of Mechanical Energy‖, International
Energy Conversion Engineering Conference at Providence RI, Aug. 16–19, 2004,
AIAA-2004-5660.
[105] Bolonkin, A.A., (2004d), ―Light Multi-Reflex Engine‖, Journal JBIS, Vol. 57, No 9/10,
pp. 353–359, 2004.
[106] Bolonkin, A.A., (2004e), ―Optimal trajectory of air and space vehicles‖, AEAT, No 2,
pp. 193–214, 2004.
[107] Bolonkin, A.A.,(2004f), ―Hypersonic Gas-Rocket Launcher of High Capacity‖, Journal
JBIS, Vol. 57, No 5/6, pp. 167–172, 2004.
[108] Bolonkin, A.A., (2004g), ―High Efficiency Transfer of Mechanical Energy‖.
International Energy Conversion Engineering Conference at Providence RI, USA. 16–
19 August, 2004, AIAA-2004-5660.
[109] Bolonkin, A.A., (2004h), ―Multi-Reflex Propulsion System for Space and Air
Vehicles‖, JBIS, Vol. 57, No 11/12, 2004, pp. 379–390.
[110] Bolonkin A.A., (2004i), Utilization of Wind Energy at High Altitude, AIAA-2004-
5705, AIAA-2004-5756, International Energy Conversion Engineering Conference at
Providence., RI, Aug.16-19. 2004. USA. http://arxiv.org .
[111] Bolonkin A., Cloutier D., (2004j). Search and Attack Strategies, AIAA Conference
Guidance, Navigation, and Control, Rhide Island, 16-19 August, 2004, Tr. #20201.
[112] Bolonkin A., Cloutier D., (2004k). Search for Enemy Targets, Technica. Report AFRLMN-EG-TR-2003-1716,
June 2002. 49 p.
[113] Bolonkin A.A., (2004k)Twenty-first century – the beginning of human immortality,
Journal ―Kybernetes‖, Vol. 33, No.9/10, 2004, pp. 1535-1542, Emerald Press,
www.emeraldinsight.com/ISSN 0368-492X.htm (English).
[114] Bolonkin A.A.,(2005a) ―High Speed Catapult Aviation‖, AIAA-2005-6221,
Atmospheric Flight Mechanic Conference – 2005, 15–18 August, 2005, USA.
[115] Bolonkin A.A., (2005b), ―Kinetic Anti–Gravitator‖, AIAA-2005-4504, 41 Propulsion
Conference, 10–12 July 2005, Tucson, Arizona, USA.
[116] Bolonkin, A.A., (2005c), ―Electrostatic Solar Wind Propulsion System‖, AIAA-2005-
3857, 41 Propulsion Conference, 10–13 July 2005, Tucson, Arizona, USA.
434 Alexander Bolonkin
[117] Bolonkin, A.A., (2005d), ―Sling Rotary Space Launcher‖, AIAA-2005-4035, 41
Propulsion Conference, 10–13 July 2005, Tucson, Arizona, USA.
[118] Bolonkin A.A., (2005e), ―Electrostatic Utilization Asteroids for Space Flight‖, 41
Propulsion conference, 10–12 July 2005, Tucson, Arizona, USA, AIAA-2005-3857.
[119] Bolonkin A.A., (2005f), ―Guided Solar Sail and Electric Generator‖, 41 Propulsion
conference, 10–12 July, 2005, Tucson, Arizona, USA, AIAA-2005-3857.
[120] Bolonkin A.A., (2005g), ―Problems of Levitation and Artificial Gravity‖, 41 Propulsion
conference, 10–12 July 2005, Tucson, Arizona, USA, AIAA-2005-3365.
[121] Bolonkin A.A., (2005h), ―Radioisotope Sail and Electric Generator‖, 41 Propulsion
conference, 10–12 July, 2005, Tucson, Arizona, USA, AIAA-2005-3653.
[122] Bolonkin A.A., Murphy R., (2005i). Geometry-Based Parametric Modeling for Single
Pursuer Multiple Evader Problems. Journal JGCD, v.28, #1, 2005
[123] Bolonkin A.A. (2006a), Book "Non-Rocket Space Launch and Flight", Elsevier,
London, 2006, 488 ps. Contents is in http://Bolonkin.narod.ru/p65.htm .
[124] Book contains more 20 new revolutionary author's concepts and ideas.
[125] Bolonkin A.A., (2006b), Beam Space Propulsion, AIAA-2006-7492, Conference
Space-2006, 18-21 Sept;, 2006, San Jose, CA, USA. http://arxiv.org , search
"Bolonkin".
[126] Bolonkin A.A., (2006c), Electrostatic AB-Ramjet Space Propulsion, AIAA/AAS
Astrodynamics Specialist Conference, 21-24 August 2006, USA. AIAA-2006-6173.
Journal "Aircraft Engineering and Aerospace Technology", Vol.79, #1, 2007.
http://arxiv.org , search "Bolonkin".
[127] Bolonkin A.A., (2006d), Electrostatic Linear Engine, AIAA-2006-5229, 42nd Joint
Propulsion Conference, 9-12 June 2006, Sacramento, USA. Journal "Aircraft
Engineering and Aerospace Technology", Vol.78, #6, 2006, pp.502-508.
[128] Bolonkin A.A., (2006e), High-Speed Solar Sail, AIAA-2006-4806, 42nd Joint
Propulsion Conference, 9-12 June 2006, Sacramento, USA. http://arxiv.org , search
"Bolonkin".
[129] Bolonkin A.A., (2006f), A New Method of Atmospheric Reentry for Space Shuttle,
AIAA-2006-6985, MAO Conference, 6-9 Sept. 2006, USA. http://arxiv.org , search
"Bolonkin".
[130] Bolonkin A.A., (2006g), Suspended Air Surveillance System, AIAA-2006-6511, AFM
Conference, 21-29 Aug. 2006, Keystone, USA. http://arxiv.org , search "Bolonkin".
[131] Bolonkin A.A., (2006h), Optimal Solid Space Tower, AIAA-2006-7717. ATIO
Conference, 25-27 Sept. 2006, Wichita, Kansas, USA. http://arxiv.org , search
"Bolonkin".
[132] Bolonkin A.A., (2006i), Theory of Space Magnetic Sail Some Common Mistakes and
Electrostatic MagSail. Presented as paper AIAA-2006-8148 to 14-th Space Planes and
Hypersonic System Conference, 6-9 November 2006, Australia. http://arxiv.org , search
"Bolonkin".
[133] Bolonkin A.A., (2006j) Micro -Thermonuclear AB-Reactors for Aerospace. Presented
as paper AIAA-2006-8104 in 14th Space Plane and Hypersonic Systems Conference, 6-
8 November, 2006, USA. http://arxiv.org , search "Bolonkin".
[134] Bolonkin A., Cathcart R., (2006k). A Low-Cost Natural Gas/Freshwater Aerial
Pipeline. http://arxiv.org, search "Bolonkin".
New Concepts, Ideas and Innovations in Aerospace… 435
[135] Bolonkin A.A., (2006 l) Cheap Textile Dam Protection of Seaport Cities against
Hurricane Storm Surge Waves, Tsunamis, and Other Weather-Related Floods.
http://arxiv.org , search "Bolonkin".
[136] Bolonkin A., Cathcart R., (2006m). The Java-Sumatra Aerial Mega-Tramway,
http://arxiv.org.
[137] Bolonkin A., Cathcart R., (2006n). Inflatable Evergreen Polar Zone Dome (EPZD)
Settlements. http://arxiv.org , search "Bolonkin".
[138] Bolonkin, A.A. and R.B. Cathcart, (2006) ―A Cable Space Transportation System at the
Earth‘s Poles to Support Exploitation of the Moon‖, Journal of the British
Interplanetary Society 59: 375-380.
[139] Bolonkin A., (2006o). Control of Regional and Global Weather. http://arxiv.org ,
search "Bolonkin".
[140] Bolonkin A., Cathcart R., (2006p). Antarctica: A Southern Hemisphere Windpower
Station? http://arxiv.org , search "Bolonkin".
[141] Bolonkin A.A., (2006q). AB Levitator and Electricity Storage. http://arxiv.org , search
"Bolonkin".
[142] Bolonkin A.A. (2006r). Simplest AB-Thermonuclear Space Propulsion and Electric
Generator. http://arxiv.org , search "Bolonkin".
[143] Bolonkin A.A., (2006s). Wireless Transfer of Electricity in Outer Space.
http://arxiv.org , search "Bolonkin".
[144] Bolonkin A.A., (2006t). Electrostatic AB-Ramjet space propulsion for interplanetary
flight, AEAT, vol. 79, No. 1, 2007, pp. 3 - 16.
[145] Bolonkin A.A., (2006u). Method of Recording and Saving of Human Soul for Human
Immortality and Installation for it. Patent application US PTO 11613380 of 12/20/06.
[146] Bolonkin, A.A. and R.B. Cathcart (2006v), ―Inflatable ‗Evergreen‘ dome settlements
for Earth‘s Polar Regions‖, Clean Technologies and Environmental Policy DOI
10.1007/s10098-006-0073-4.
[147] Cathcart R., Bolonkin A., (2006w), The Golden Gate Textile Barrier: Preserving
California Bay of San Francisco from a Rising North Pacific Ocean. http://arxiv.org.
Search: "Bolonkin".
[148] Cathcart R., Bolonkin A., (2006x), Ocean Terracing, http://arxiv.org . Search:
"Bolonkin".
[149] Book (2006),: Macro-Engineering - A challenge for the future. Collection of articles.
Eds. V. Badescu, R. Cathcart and R. Schuiling, Springer, 2006. (Collection contains
two Bolonkin's articles: Space Towers; Cable Anti-Gravitator, Electrostatic Levitation
and Artificial Gravity).
[150] Bolonkin A.A., (2007a). AB Levitrons and their Applications to Earth‘s Motionless
Satellites, http://arxiv.ru , search: Bolonkin.
[151]Bolonkin A.A., (2007b). Passenger life-saving in a badly damaged aircraft scenario,
AIAA-2007-5844, http://arxiv.ru , search: Bolonkin.
[152]Bolonkin A.A., (2007c). Optimal Electrostatic Space Tower (Mast, New Space
Elevator), AIAA-2007-6201, http://arxiv.ru , search: Bolonkin.
[153]. Bolonkin A.A., (2007d). Electrostatic Space Climber, AIAA-2007-5838,
http://arxiv.ru , search: Bolonkin.
[154]Bolonkin A.A., (2007e). Inflatable Dome for Moon, Mars, Asteroids and Satellites,
AIAA-2007-6262, http://arxiv.ru , search: Bolonkin.
436 Alexander Bolonkin
[155]Bolonkin A.A., (2007f). Human Immortality and Electronic Civilization, 3-rd Edition,
Lulu, 2007, 66 pgs., (Enflish and Russian), http://www.lulu.com search ―Bolonkin‖.
[156]Bolonkin A.A., (2007g). Memories of Soviet Political Prisoner, Lulu, 2007, 66 pgs.,
(Enflish and Russian), http://www.lulu.com search ―Bolonkin‖. English is translated
from same Russian book, New your, 1991.
[157] Calasso F.E., (1989), Advanced Fibers and Composite, Gordon and Branch Scientific
Publisher, New York, 1989.
[158] Carbon and High Performance Fibers, (1995), Directory, NY 1995, Chapman and
Hall, 6th ed., New York.
[159] Concise Encyclopedia of Polymer Science and Engineering, (1990), Ed. J. I.
Kroschwitz, 1990. New York.
[160] Clarke A.C.: Fountains of Paradise, Harcourt Brace Jovanovich, New York, 1978.
[161] Dresselhous, M.S.,(2000), Carbon Nanotubes, Springer, New York, 2001.
[162] Fedorov V.D., (1981), Basis of Rocket Flight, Moscow, Nauka.(Russian).
[163] Handbook of Physical Quantities, Ed. Igor S. Grigoriev, 1997, CRC Press, USA.
[164] Harris, J.T. (1973), Advanced Material and Assembly Methods for Inflatable Structures.
AIAA, Paper No. 73-448.
[165] Johnson A., Space Research: Organizing for Economical Efficiency. Presented as paper
AIAA-2006-7224 in Conference "Space-2006", 19-21 September 2006, San Diego,
California, USA.
[166] Johnson A., Space research: problems of efficiency. Journal "Actual Problems of
Aviation and Aerospace System", No.1, 2007. http://www.kcn.ru/tat_en/science/ans
/journals/rasj_cnt/07_1_10.html
[167] Kikoin I.K., (1976), Table of Physical Magnitudes, Moscow, Atomic Publish
House.(Russian).
[168] Landis G.A., (2004), Interstellar Flight by Particle Beam, Acta Astronautica, Vol. 55,
pp.931 - 934.
[169] Landis G., (2000). "Dielectric Films for Solar- and Laser-pushed Lightsails," AIP
Conference Proceedings Volume 504, pp. 989-992; Space Technology and Applications
International Forum (STAIF-2000), Jan. 30 - Feb. 3, Albuquerque NM.
[170] Landis Geoffrey A., Cafarelli Craig, (1999). The Tsiolkovski Tower Re-Examined,
JBIS, Vol. 32, pp. 176 -180, 1999.
[171] Landis, Geoffrey A. and Cafarelli, Craig, (1995), "The Tsiolkovski Tower," paper IAF95-V.4.07,
46th International Astronautics Federation Congress, Oslo Norway, 2-6 Oct.
1995. There is also an errata to this paper, which was published in JBIS: Landis,
Geoffrey A., (2005),"Correction," Journal of the British Interplanetary Society, Vol.
58, p. 58.
[172] Landis, Geoffrey A., (1998), "Compression Structures for Earth Launch," paper AIAA98-3737,
24th AIAA/ASME/SAE/ASEE Joint Propulsion Conf., July 13-15, Cleveland
OH.
[173] Nishikawa K., Wakatani M., Plasma Physics, Spring, 2000.
[174] Omidi N. and Karimabadi H., (2003), ―Electrostatic Plasma Sail‖, AIAA 2003-5227,
2003. 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 20-23
July 2003, Hurtisville, Alabama. Contains a principal scientific mistakes.
[175] Regan F.J., Anandakrishnan S.M., Dynamics of Atmospheric Re-Entry, AIAA, 1993
New Concepts, Ideas and Innovations in Aerospace… 437
[176] Shortley G., Williams D., Elements of Physics, Prentice-Hall, Inc., Englewood Cliffs,
New Jersey, 1971, USA.
[177] Smitherman D.V., Jr., Space Elevators, NASA/CP-2000-210429, 2000.
[178] Tsiolkovski K.E.: ‖Speculations about Earth and Sky on Vesta,‖ Moscow, Izd-vo AN
SSSR, 1959; Grezi o zemle I nebe (in Russian), Academy of Sciences, U.S.S.R.,
Moscow, p.35, 1999.
Russian Works
[179] Tsiolkovski, K.E. (1959),‖Speculations about Earth and Sky on Vesta‖, Moscow, Izdvo
AN SSSR, 1959; Grezi o zemle i nebe (in Russian), Academy of Sciences, USSR.,
Moscow, p. 35, 1999.
[180] Mayboroda A., Zero Gravity on Earth, ―Yuniy Tehnik‖ (―Young Technician‖), No. 10,
October 1988, Moscow (in Russian).
[181] Pokrovskii G.I., (1964), Space Tower, TM, ("Technology for Youth"), No. 10, (in
Russian).
[182] Poliakov G., (1977), Space Necklace of Earth, TM, ("Technology for Youth"), No. 4,
(in Russian).
[183] Yunitskii A., (1982), "General Planetary Transport System", "TM" ("Technology for
Youth"), No. 6,) (in Russian). (see last four Russian works in:
http://www.ipu.ru/stran/bod/ing/sovet2.htm, Pictures: http://www.ipu.ru/stran/bod/ing
/sovet_ris.htm)
NIAC Reports
[184] http://auditing-science.narod.ru or http://www.geocities.com/auditing.science/
[185] Christensen C., ―Ultralight Solar Sail for Interstellar Travel‖, http://NASANIAC.narod.ru
[186] Hose S. D., ―Antimatter Drive Sail for Deep Space Missions‖, http://NASANIAC.narod.ru
[187] Landis G. A., ―Advanced Solar and Laser Pushed Lightsail Concepts‖, http://NASANIAC.narod.ru
[188] Miller D. W., ―Electromagnetic Formation Flight‖, http://NASA-NIAC.narod.ru
[189] Zubrin, R., ―The Magnetic Sail‖. http://NASA-NIAC.narod.ru.
[190] About NIAC: GO TO: http://auditing-science.narod.ru or
http://www.geocities.com/auditing.science/, http://NASA-NIAC.narod.ru
Some Popular Bolonkin's Publications and Publications about His Ideas
[191] Personal site: Bolonkin A.A., http://Bolonkin.narod.ru
[192] Bibliography (about the author and discussing his ideas) publication in Russian press
and Internet in 1994 - 2004 (http://www.km.ru, http://pravda.ru, http://n-t.ru, ets.
Search: Bolonkin)/
[193] Bolonkin A.A., Our children may be a last people generation, Literary newspaper,
10/11/95, #41 (5572), Moscow, Russia (Russian).
438 Alexander Bolonkin
[194] Bolonkin A.A., Stop the Earth. I step off. People Newspaper, Sept.,1995. Minsk,
Belorussia (Russian).
[195] Bolonkin A.A., End of Humanity, but not End of World. New Russian Word, 3/6/96,
p.14, New York, USA (Russian).
[196] Bolonkin A.A., Natural Human Purpose is to be God. http://Bolonkin.narod.ru
(Russian).
[197] Bolonkin A.A., American and Russian Science.(English). http://Bolonkin.narod.ru.
[198] Bolonkin A.A., Locate the God into Computer-Internet Network (in Russian).
http://Bolonkin.narod.ru.
[199] Blekherman A., Short biography of Dr. A. Bolonkin. (English, Russian)
http://Bolonkin.narod.ru
[200] Dr.Sci. M. Krinker, World Space Congress-2002 (about 9 Bolonkin's scientific works
presented to Congress). http://Bolonkin.narod.ru (Russian).
[201] Ruduyk B., New ideas of Dr. Bolonkin, Newspaper "Fact", Ukraine (in Ukraine).
http://Bolonkin.narod.ru.
[202] Kurolenko N., Electronic Society, News paper "Kievskie Vedomosti", C. Kiev, Ukraine,
27 May, 2002. http://Bolonkin.narod.ru.
[203] Bay E., Our soul is only set our knowledge (about ideas of A. Bolonkin). Newspaper
"Literary Newspaper". 10 July, 2002. Moscow (in Russian).
[204] Golovkov A., Time for thinking, Magazime "Ogonek", 1988, Moscow, Russia (in
Russian). http://Bolonkin.narod.ru .
[205] Levin V., "Take-off and Landing" (article from magazine "Vestnik" about Bolonkin.
1992)(Russian).
[206] Bolonkin A.A., Peculiarities of Soviet and American Sciences. (Russian).
http://Bolonkin.narod.ru
[207] Bolonkin A.A., Memoirs of Soviet Political Prisoner (English).
http://Bolonkin.narod.ru.
[208] http://wikipedia.org search ―Bolonkin‖, http://Coogle.com search ―Bolonkin‘
