1

Asteroids as Propulsion Systems of Space Ships
Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
World Space Congress 2002, Houston, TX, United States, 10-19 Oct. 2002; JBIS, Volume 56, 98-107 , 20030101; 2003
Currently, rockets are used to change the trajectory of space ships and probes. This method is very expensive and requires a lot of fuel, which limits the feasibility of space stations, interplanetary space ships, and probes. Sometimes space probes use the gravity field of a planet However, there am only nine planets in the Solar System, all separated by great distances. There are tons of millions of asteroids in outer space. This paper offers a revolutionary method for changing the trajectory of space probes. The method uses the kinetic or rotary energy of asteroids, comet nuclei, meteorites or other space bodies (small planets, natural planetary satellites, space debris, etc.) to increase (to decrease) ship (probe) speed up to 1000 m/sec (or more) and to achieve any new direction in outer space. The flight possibilities of space ships and probes are increased by a factor of millions.
Document ID: 20030018886
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2005-08-25

2.

Optimal Inflatable Space Towers with 3 - 100 km Height
Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
World Space Congress 2002, Houston, TX, United States, 10-19 Oct. 2002; JBIS, Volume 56, 87-97 , 20030101; 2003
Theory and computations are provided for building inflatable space towers 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, and for radio, television, and communication transmissions. These towers can also be used to launch space ships and Earth satellites. These projects are not expensive and do not require rockets. They require thin strong films composed from artificial fibers and fabricated by current industry. The towers can be built using present technology. The 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 work at high altitudes; 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. The tower is separated into sections and has special protection mechanisms in case of damage. Problems involving security, control, repair, and stability of the proposed towers are addressed in other publications. The author is prepared to discuss these and other problems with serious organizations desiring to research and develop these projects.
Document ID: 20030018887
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2005-08-25

3.

Employment of Asteroids for Movement Space Ship and Probes
Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
IAC-02-S.6.04; 53rd International Astronautical Congress: The World Space Congress, Houston, TX, United States, 10-19 Oct. 2002 , 20020101; 2002
At present, rockets are used to change the trajectory of space ships and probes. This method is very expensive and requires a lot of fuel, which limits the feasibility of space stations, interplanetary space ships, and probes. Sometimes space probes use the gravity field of a planet. However, there are only 9 planets in our solar system and they are separated by great distances. There are tens of millions of asteroids in outer space. The author offers a revolutionary method for changing the trajectory of space probes. This method uses the kinetic or rotary energy of asteroids, meteorites or other space bodies (small planets, natural planet satellites, etc.). to increase (to decrease) ship (probe) speed up to 1000 m/sec (or more) and to get any new direction in outer space. The flight possibilities of space ships and probes are increased by a factor of millions.
Document ID: 20030018908
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2005-08-25

4.

Non-Rocket Missile Rope Launcher
Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
IAC-02-S.P.14; 53rd International Astronautical Congress: The World Space Congress, Houston, TX, United States, 10-19 Oct. 2002 , 20020101; 2002
The method, installation, and estimation for delivering payload and missiles into outer space are presented. This method uses, in general, the engines and straight or closed-loop cables disposed on a planet surface. The installation consists of a space apparatus, power drive stations located along trajectory of the apparatus, the cables connected to the apparatus and to the power stations, a system for suspending the cable, and disconnected device. The drive stations accelerate the apparatus up to hypersonic speed. The estimations and computations show the possibility of making these projects a reality in a short period of time (see attached project: launcher for missiles and loads). The launch will be very cheap $1-$2 per LB. We need only light strong cable, which can be made from artificial fibers, whiskers, nanotubes, which exist in industry and scientific laboratories.
Document ID: 20030018907
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2005-08-25

5.

Non-Rocket Earth-Moon Transport System
Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
COSPAR-02-B0.3-F3.3-0032-02; 34th COSPAR Scientific Assembly: The World Space Congress 2002, Houston, TX, United States, 10-19 Oct. 2002 , 20020101; 2002
This paper proposes a new method and transportation system to travel to the Moon. This transportation system uses a mechanical energy transfer and requires only minimal energy so that it provides a 'Free Trip' into space. The method uses the rotary and kinetic energy of the Moon. This paper presents the theory and results of computations for the project provided Free Trips (without rockets and spend a big energy) to the Moon for six thousand people annually. The project uses artificial materials like nanotubes and whiskers that have a ratio of tensile strength to density equal 4 million meters. In the future, nanotubes will be produced that can reach a specific stress up 100 millions meter and will significantly improve the parameters of suggested project. The author is prepared to discuss the problems with serious organizations that want to research and develop these innovations.
Document ID: 20030018893
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2005-08-25

6.

Inexpensive Cable Space Launcher of High Capability
Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
IAC-02-V.P.07; 53rd International Astronautical Congress: The World Space Congress, Houston, TX, United States, 10-19 Oct. 2002 , 20020101; 2002
This paper proposes a new method and transportation system to fly into space, to the Moon, Mars, and other planets. This transportation system uses a mechanical energy transfer and requires only minimal energy so that it provides a 'Free Trip' into space. The method uses the rotary and kinetic energy of planets, asteroids, moons, satellites and other natural space bodies. computations for the following projects: 1. Non-Rocket Method for free launch of payload in Space and to other planets. The low cost project will accommodate one hundred thousand tourists annually. 2. Free Trips to the Mars for two thousand annually. 3. Free Trips to the Moon for ten thousand people annually. The projects use artificial materials like nanotubes and whiskers that have a ratio of tensile strength to density equal 4 million meters. In the future, nanotubes will be produced that can reach a specific stress up 100 millions meter and will significantly improve the parameters of suggested projects. The author is prepared to discuss the problems with serious organizations that want to research and develop these inventions.
Document ID: 20030018889
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2005-08-25

7.

Transport System for Delivery Tourists At Altitude 140 km
Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
IAC-02-IAA.1.3.03; 53rd International Astronautical Congress: The World Space Congress 2002, Houston, TX, United States, 10-19 Oct. 2002 , 20020101; 2002
The author offers a new method and installation for flight in space. This method uses the centrifugal force of a rotating circular cable that provides a means for the launch of a payload into outer space, to keep the fixed space stations at high altitudes (up to 200 km). The method may also be useful for landing to space bodies, for launching of the space ships (crafts), and for moving and accelerating other artificial apparatuses. The offered installation may be used as a propulsion system for space ships and/or probes. This system uses the material of any space body (i.e. stones) for acceleration and change of the space vehicle trajectory. The suggested system may be also used as a high capacity energy accumulator.
Document ID: 20030018888
No Digital Version Available - Order This Document from CASI
Updated/Added to NTRS: 2005-08-25

8.

Optimal Pitch Thrust-Vector Angle and Benefits for all Flight Regimes
Gilyard, Glenn B.; Bolonkin, Alexander
NASA Center for AeroSpace Information (CASI)
NASA/TM-2000-209021; NAS 1.15:209021; H-2402 , 20000301; March 2000
The NASA Dryden Flight Research Center is exploring the optimum thrust-vector angle on aircraft. Simple aerodynamic performance models for various phases of aircraft flight are developed and optimization equations and algorithms are presented in this report. Results of optimal angles of thrust vectors and associated benefits for various flight regimes of aircraft (takeoff, climb, cruise, descent, final approach, and landing) are given. Results for a typical wide-body transport aircraft are also given. The benefits accruable for this class of aircraft are small, but the technique can be applied to other conventionally configured aircraft. The lower L/D aerodynamic characteristics of fighters generally would produce larger benefits than those produced for transport aircraft.
Document ID: 20000034897
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Updated/Added to NTRS: 2005-08-25

9.

Optimal Pitch Thrust-Vector Angle and Benefits for all Flight Regimes
Gilyard, Glenn B.; Bolonkin, Alexander
NASA Dryden Flight Research Center
NASA Technical Memorandum , 2000-03-01
The NASA Dryden Flight Research Center is exploring the optimum thrust-vector angle on aircraft. Simple aerodynamic performance models for various phases of aircraft flight are developed and optimization equations and algorithms are presented in this report. Results of optimal angles of thrust vectors and associated benefits for various flight regimes of aircraft (takeoff, climb, cruise, descent, final approach, and landing) are given. Results for a typical wide-body transport aircraft are also given. The benefits accruable for this class of aircraft are small, but the technique can be applied to other conventionally configured aircraft. The lower L/D aerodynamic characteristics of fighters generally would produce larger benefits than those produced for transport aircraft.
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Updated/Added to NTRS: 2004-09-21

10.

Estimated Benefits of Variable-Geometry Wing Camber Control for Transport Aircraft
Bolonkin, Alexander; Gilyard, Glenn B.
NASA Center for AeroSpace Information (CASI)
NASA/TM-1999-206586; H-2368; NAS 1.15:206586 , 19991001; October 1999
Analytical benefits of variable-camber capability on subsonic transport aircraft are explored. Using aerodynamic performance models, including drag as a function of deflection angle for control surfaces of interest, optimal performance benefits of variable camber are calculated. Results demonstrate that if all wing trailing-edge surfaces are available for optimization, drag can be significantly reduced at most points within the flight envelope. The optimization approach developed and illustrated for flight uses variable camber for optimization of aerodynamic efficiency (maximizing the lift-to-drag ratio). Most transport aircraft have significant latent capability in this area. Wing camber control that can affect performance optimization for transport aircraft includes symmetric use of ailerons and flaps. In this paper, drag characteristics for aileron and flap deflections are computed based on analytical and wind-tunnel data. All calculations based on predictions for the subject aircraft and the optimal surface deflection are obtained by simple interpolation for given conditions. An algorithm is also presented for computation of optimal surface deflection for given conditions. Benefits of variable camber for a transport configuration using a simple trailing-edge control surface system can approach more than 10 percent, especially for nonstandard flight conditions. In the cruise regime, the benefit is 1-3 percent.
Document ID: 19990090019
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Updated/Added to NTRS: 2005-08-25

11.

Estimated Benefits of Variable-Geometry Wing Camber Control for Transport Aircraft
Bolonkin, Alexander; Gilyard, Glenn B.
NASA Dryden Flight Research Center
NASA Technical Memorandum , 1999-10-01
Analytical benefits of variable-camber capability on subsonic transport aircraft are explored. Using aerodynamic performance models, including drag as a function of deflection angle for control surfaces of interest, optimal performance benefits of variable camber are calculated. Results demonstrate that if all wing trailing-edge surfaces are available for optimization, drag can be significantly reduced at most points within the flight envelope. The optimization approach developed and illustrated for flight uses variable camber for optimization of aerodynamic efficiency (maximizing the lift-to-drag ratio). Most transport aircraft have significant latent capability in this area. Wing camber control that can affect performance optimization for transport aircraft includes symmetric use of ailerons and flaps. In this paper, drag characteristics for aileron and flap deflections are computed based on analytical and wind-tunnel data. All calculations based on predictions for the subject aircraft and the optimal surface deflection are obtained by simple interpolation for given conditions. An algorithm is also presented for computation of optimal surface deflection for given conditions. Benefits of variable camber for a transport configuration using a simple trailing-edge control surface system can approach more than 10 percent, especially for nonstandard flight conditions. In the cruise regime, the benefit is 1�3 percent.
View PDF File
Updated/Added to NTRS: 2004-09-21

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