Non-Rocket Space Launch and Flight

Name: Non-Rocket Space Launch and Flight
Brand: Elsevier
Price: 240.0 EUR
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Alexander A. Bolonkin(Autor*in)

Elsevier (Verlag)

Erschienen am 14. Mai 2014

485 Seiten

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978-0-08-045875-5 (ISBN)

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Inhalt

Front cover
Title page
Copyright
Table of contents
Abstract
Preface
1 Space elevator, transport system for space elevator, and tether system
Summary
1.1 Brief history
1.2 Short description
1.3 Transport system for the space elevator
Nomenclature (metric system)
1.3.1 Introduction
1.3.2 Brief history
1.3.3 Brief description, theory, and computation of innovations
1.4 Free trip to space (Project 1)
1.4.1 Description
1.4.2 Theory and computation (in metric system)
1.4.3 Transport system for space elevator (Project 1)
1.4.3.1 Main results of computation
1.4.4 Estimations of installation cost and production cost of delivery
1.4.4.1 Cost of suggested space transport installation
1.4.4.2 Cost of delivery
1.5 Delivery system for free round trip to Mars (Project 2)
1.5.1 Technical parameters of Mars transport system
1.6 Free trip to Moon (Project 3)
1.6.1 Technical parameters
1.7 Discussion
1.7.1 Cable problems
1.7.2 Data that can be used for computation
1.8 Conclusions
1.9 Tether system
1.9.1 Short description
1.9.1.1 Tidal stabilization for altitude control
1.9.1.2 Electrodynamic tethers
1.9.1.3 Rotovators
1.9.1.4 Space elevators
1.9.2 Problems
References
2 Cable space accelerator
Summary
2.1 Introduction
2.2 Description of suggested launcher
2.2.1 Brief description
2.2.2 Advantages
2.2.3 Cable discussing
2.3 Theory of the cable launcher
2.3.1 Formulas for estimation and computation (in metric system)
2.3.1.1 Relative cross-section area
2.3.1.2 Safety cable speed
2.3.1.3 Energy
2.3.1.4 Maximum distance
2.3.1.5 Amount of sag ?H of the cable
2.3.1.6 Flight range
2.3.1.7 Wave drag
2.3.1.8 Loss of speed
2.3.1.9 Cable friction
2.3.1.10 Mass of cable
2.3.1.11 Energy
2.3.1.12 Subsonic speed
2.3.1.13 Last drive station
2.4 Projects
2.4.1 Project 1
2.4.1.1 The launch of tourists into space
2.4.1.2 Economic efficiency
2.4.2 Project 2
2.4.2.1 The launcher for payload (projectile) with high
2.4.2.2 Economic efficiency
2.5 General discussion
References
3 Circle launcher and space keeper
Summary
Nomenclature
3.1 Introduction
3.2 Description of circle launcher
3.3 Theory of circle launcher
3.3.1 Estimation of cable friction due to the air
3.4 Case studies
3.4.1 Project 1
3.4.1.1 Space station for tourists or a scientific laboratory at an altitude of 140 km
3.4.1.2 Economic estimations of these projects for space tourisms
3.4.1.3 Discussion of Project 1
3.4.2 Project 2
3.4.2.1 Semi-circle of a radius 1000 km (625 miles) for delivering passengers to a distance of 2000 km (1250 miles) through space
3.4.2.2 Estimation of economic efficiency
3.4.2.3 Discussion of Project 2
3.4.3 Project 3
3.4.3.1 Circle around the Earth at an altitude of 200 km (125 miles) for 8-10 scientific laboratories
3.4.3.2 Discussion of Project 3
3.4.4 Project 4
3.4.4.1 Using the cable circle as a propulsion system and energy storage system
3.5 Discussion, summary, and conclusions
References
4 Optimal inflatable space towers
Summary
4.1 Introduction
4.1.1 Brief history
4.1.2 The tower applications
4.2 Description of innovation and problem
4.2.1 Tower structure
4.2.2 Filling gas
4.2.3 Tower material
4.2.4 Tower safety
4.2.5 Tower stability
4.2.6 Tower construction
4.2.7 Tower cost
4.3 Theory of inflatable towers (all equations are given in metric system)
4.3.1 The pressure of any gas in a column versus altitude
4.3.2 Optimal cover thickness and tower radius
4.3.3 Tower lift force F
4.3.4 Base area for a given top load W [kg]
4.3.5 Mass of cover
4.3.6 The thickness of a tower cover
4.3.7 Maximum safety bending moment
4.3.8 Gas mass M into tower
4.3.9 Base tower radius
4.3.10 Tower mass
4.3.11 Distance L of Earth
4.4 Projects
4.4.1 Project 1: A simple air tower of 3 km height (base radius 5 m, 15 ft, and K = 0.1)
4.4.1.1 Results of computations
4.4.1.2 Economic efficiency
4.4.2 Project 2: Helium tower 30 km (base radius is 5 m, 15 ft, and K = 0.1)
4.4.2.1 Results of computation
4.4.3 Project 3: Air-hydrogen tower 100 km (base radius of air part is 35 m and the hydrogen part has base radius 5m)
4.4.3.1 Air part (0-15 km)
4.4.3.2 Hydrogen part (15-100 km)
4.5 Conclusion
References
5 Kinetic space towers
Summary
5.1 Introduction
5.2 Description of suggested launcher
5.2.1 Brief description of innovation
5.2.1.1 Advantages
5.2.1.2 Cable discussing
5.3 Theory of the kinetic tower and launcher
5.3.1 Lift force of the kinetic tower
5.3.2 Lift force in a constant gravity field
5.3.3 Maximum tower height or minimum cable speed in a constant gravity field
5.3.4 Kinetic lift force in a variable gravity field and for the rotary Earth
5.3.5 Estimation of cable friction in the air
5.3.6 People security
5.4 Projects
5.4.1 Project 1: Kinetic tower of height 4km
5.4.2 Project 2: Kinetic tower of height 75km
5.4.3 Project 3: Multi-stage kinetic tower of height 225 km
5.4.4 Project 4: Kinetic tower with height 160,000 km
5.4.5 Project 5: Kinetic tower as space launcher
5.5 Discussion
References
6 Gas tube hypersonic launcher
Summary
Nomenclature (metric system)
6.1 Introduction
6.1.1 Short history of the high-speed gun
6.2 Description
6.3 Methods of estimation and results of computation
6.3.1 Estimation of missile velocity
6.3.2 Estimation of tube length
6.3.3 Loss of velocity in the atmosphere
6.3.4 Load delivered to orbit
6.3.4.1 Example of use
6.4 Production cost of delivery
6.4.1 Excess of energy
6.4.2 Launcher as an accumulator of energy
6.4.3 Gun recoil
6.4.4 Tube curvature
6.4.5 Wall thickness
6.4.6 Gas friction
6.5 Advantages of the proposed space launcher
6.6 Discussion
References
7 Earth-Moon cable transport system
Summary
7.1 Introduction
7.2 Brief history
7.3 Brief description, theory, and computation of innovations
7.4 Theory of optimal cable from earth to moon
7.5 Technical parameters of projects
7.6 Conclusion
References
8 Earth-Mars cable transport system
Summary
8.1 Introduction
8.2 Brief description
8.3 Theory of Earth-Mars equal stress cable
8.4 Project
8.4.1 Earth-Mars non-rocket transport system
8.5 Conclusion
References
9 Kinetic anti-gravitator
Summary
Nomenclature
9.1 Introduction
9.2 Brief description of the installation
9.3 Theory of the kinetic anti-gravitator
9.3.1 Push force for immobile object
9.3.1.1 Repulsive (repel, push) force in space without gravitation
9.3.1.2 Repulsive force in constant gravity field
9.3.1.3 Repulsive force in variable gravity field and rotary Earth
9.3.2 Repulsive force for a mobile object
9.3.3 Restore force
9.3.4 Air drag of the cable
9.3.4.1 The air drag of a double subsonic cable
9.3.4.2 Air drag of supersonic and hypersonic double cable
9.3.5 Computations
9.3.6 Calculations
9.4 Advantages of offered method
9.5 Applications
9.5.1 VTOL conventional aircraft
9.5.2 Non-rocket space apparatus
9.5.3 Flying "superman"
9.5.4 Walking "superman" or vehicle
9.5.5 Jumping (pogo-stick) "superman"
9.5.6 Jumping vehicle
9.5.7 Long arm (long hand)
9.5.8 High-altitude crane
9.5.9 High tower
9.5.10 The construction of the Artsutanov space elevator without rockets
9.6 Discussion
9.7 Conclusion
References
10 Centrifugal space launchers
Summary
Nomenclature
10.1 Introduction
10.2 Description of innovative launcher
10.2.1 Ground sling launcher
10.2.2 Aircraft sling launcher
10.2.3 Advantages
10.2.4 Cable (sling) discussion
10.3 Theory of the sling launcher
10.3.1 Formulas for estimation and computation (in metric system)
10.3.1.1 Centrifugal force
10.3.1.2 Optimal relative sling cross-section area
10.3.1.3 Air drag
10.3.1.4 Flight angle of cone
10.3.1.5 Vacuum
10.3.1.6 Engine power
10.3.1.7 Estimation of tourist trajectory
10.4 Projects
10.4.1 Project 1
10.4.1.1 Computations
10.4.1.2 Discussion of Project 1
10.4.2 Project 2
10.4.2.1 Space projectile launcher with a sling made from whiskers
10.4.2.2 Computation
10.4.2.3 Economic efficiency
10.4.2.4 Discussion
10.4.3 Project 3
10.4.3.1 The launcher for space tourists with a sling made from nanotubes
10.4.3.2 Computation
10.4.3.3 Discussion
10.4.4 Project 4
10.4.4.1 The launch of space tourists accelerated by subsonic aircraft with a sling made from whiskers
10.4.4.2 Computation
10.4.4.3 Discussion
10.4.4.4 Economic efficiency
10.5 General discussion
References
11 Asteroids as propulsion system of space ships
Summary
11.1 Introduction
11.2 Connection method
11.2.1 Description of utilization
11.2.2 Theory and computation
11.3 Project
11.4 Discussion
11.4.1 Estimation of the probability of meeting a small asteroid
11.4.2 Cable
11.5 Conclusion
References
12 Multi-reflex propulsion systems for space and air vehicles and energy transfer for long distance
Summary
12.1 Introduction
12.1.1 Short history
12.1.2 Brief information about light and light devices
12.2 Description of innovation
12.2.1 Multi-reflex launch installation of a space vehicle
12.2.1.1 Cell mirrors
12.2.1.2 Laser ring
12.2.1.3 Light lock
12.2.2 Space beam transfer
12.2.3 Aviation and energy air transfer
12.3 Theory (estimation) of multi-reflex launching and beam transfer
12.3.1 Attenuation of beam
12.3.2 Change in beam power
12.3.3 Multi-reflex light pressure
12.3.4 Limitation of reflection number
12.3.5 Coefficient of efficiency
12.3.6 Focusing the beam
12.3.7 Some computations
12.4 Discussion
12.4.1 General discussion
References
13 Electrostatic solar wind propulsion
Summary
13.1 Introduction
13.1.1 General
13.1.2 History
13.1.3 Brief information about solar wind
13.2 Brief description of the propulsion system
13.2.1 Space propulsion system
13.2.2 Steerability
13.2.3 Ball discharge
13.2.4 Blockading of the ball charge
13.2.5 Interstellar propulsion system
13.3 Basic theories of the solar wind installation and main estimations and computations
13.3.1 Note on general theory
13.3.2 Minimum neutral sphere around a charged ball
13.3.2.1 Model 1: Constant particle density
13.3.2.2 Model 2:Variable particle density
13.3.3 Electrostatic sail drag
13.3.4 The ball stress, cover thickness, and ball mass
13.3.5 Probe acceleration, speed, and flight time
13.3.6 Absorption of particles by ball cover
13.3.7 Initial expenditure of electrical energy needed to charge the ball
13.3.8 Notes about thermonuclear propulsion from solar wind
13.3.9 Charging the ball
13.4 Discussion
13.4.1 Possible limitations
13.4.2 Comparison with other works
13.5 Conclusion
References
14 Electrostatic utilization of asteroids for space flight
Summary
14.1 Introduction
14.2 Description of utilization
14.3 Theory and computation (in metric system)
14.3.1 The electrostatic force
14.3.2 Computation of space apparatus trajectories
14.3.3 Initial expenditure of electrical energy needed to charge of the ball
14.3.4 The ball stress, cover thickness, and ball mass
14.3.5 Landing on and launching the space apparatus from asteroids and small planets
14.4 Project
14.5 Discussion
14.5.1 Estimation of probability of meeting a small asteroid
14.5.2 Charging the ball
14.5.3 Blockading of the ball charge
References
15 Electrostatic levitation on the earth and artificial gravity for space ships and asteroids
Summary
15.1 Introduction
15.2 Brief description of innovation
15.3 Theory of an electrostatic lift force and results of computations (in metric system)
15.3.1 Brief information about electric charges, electrical fields, and electric corona
15.3.2 Size of corona (ionized sphere) and safety of a ball of electric intensity
15.3.3 For a cylindrical cable or belt
15.3.4 Discharging by corona
15.3.5 Some data about the ball material
15.3.6 The half-life of the charge
15.3.6.1 Spherical ball
15.3.6.2 Half-life of cylindrical tube
15.3.7 Rupture (breakthrough) of insulator
15.3.8 Levitation between flat net and ground surface
15.3.9 Electrostatic levitation of a train
15.3.10 Top tube highway
15.3.11 Spherical main ball on mast and air balloon
15.3.12 Small spherical lifting balls
15.3.13 Long (a « l) cylindrical lifting belt
15.3.14 Aerodynamics of the levitated vehicles
15.3.15 Control and stability
15.3.16 Flight in thunderstorms
15.3.17 Charging
15.3.18 Safety
15.3.19 Charged ball as an accumulator of energy
15.4 Projects
15.4.1 Levitation highway
15.4.2 Levitating tube highway
15.4.3 Charged ball located on a high mast or tower
15.4.4 Levitation in low cumulonimbus and thunderstorm clouds
15.4.5 Artificial gravity on space ship's or asteroids
15.4.6 Charged ball as an accumulator of energy and rocket engine
15.5 Discussion
References
16 Guided solar sail and energy generator
Summary
16.1 Description of method and innovations
16.1.1 Introduction
16.2 Description of innovation and their advantages
16.3 Further development
References
17 Radioisotope space sail and electro-generator
Summary
17.1 Description of method and innovations
17.1.1 Brief history of innovation
17.2 General information about the isotope sail
17.3 Description of new method, installation, and innovation
17.4 Improvements to the radioisotope sail
17.5 Possibility of electric power
17.5.1 Heating
17.6 Equation for computation of conventional IsoSail
17.6.1 Electric power of conventional IsoSail
17.6.2 Heating a conventional Isosail
17.7 Conclusion
References
18 Electrostatic solar sail
Summary
18.1 Introduction
18.2 Brief description of the innovations
18.3 Theory of estimation and computation
18.3.1 The sail
18.3.2 Initial expenditure of electrical energy to charge of the ball
18.3.3 The ball stress, cover thickness, and ball mass
18.3.4 Technology
18.3.5 Artificial Moon
References
19 Utilization of space
Summary
19.1 Recombination space jet propulsion engine
19.1.1 Summary
19.1.2 Description of method and innovation
19.1.2.1 Introduction
19.1.2.2 Description of innovation
19.2 Utilization of high-altitude mirror for lighting in local Earth areas
19.2.1 Summary
19.2.2 Description of method and innovations
19.2.2.1 Introduction
19.2.2.2 Description of innovations and their advantages
19.3 Electronic sail
19.3.1 Summary
19.3.2 Brief description of innovation
19.4 In outer space without a space suit?
19.4.1 Summary
19.4.2 Brief description of innovation
19.5 Electrostatic space radiator
References
Attachments: Non-conventional and non-rocket flight on Earth
1 Air cable transport and bridges
Summary
A1.1 Introduction
A1.2 Short description of installation
A1.3 Advantages
A1.3.1 Airlines
A1.3.2 Bridge or underground tunnel
A1.3.3 Surface transport (movement) system
A1.3.4 Air gas line
A1.4 Formulas for estimation and computation (in metric system)
A1.5 Cable problems
A1.6 Data which can be used for computation
A1.7 Projects
A1.7.1 Project 1: Air line from New York to Washington (340 km)
A1.7.1.1 Production cost of one passenger delivered
A1.7.2 Project 2: Airline from New York to Paris (6200 km)
A1.7.2.1 Economical estimation
A1.7.3 Project 3: Air bridge
A1.7.3.1 Economic estimation
A1.7.4 Project 4: Ground vehicles (for example, auto highway)
A1.7.5 Project 5: Gas line of the 2000 km (1250 miles) and capability of carrying 20 billion cubic meters/year
A1.7.5.1 Technical data
A1.7.5.2 Economical estimation
A1.7.5.3 Additional possibility
A1.8 Conclusion
References
2 High-speed catapult aviation
Summary
A2.1 Introduction
A2.2 Brief description of the innovation
A2.3 Theory of KV and a general estimation of flight data (in metric system)
A2.3.1 Maximum range
A2.3.2 Maximum acceleration
A2.3.3 Average speed
A2.3.4 Horizontal turn
A2.4 Advantages
A2.5 Project
A2.5.1 Economical efficiency
A2.6 Discussion of problems
References
3 Light multi-reflex engine
Summary
A3.1 Introduction
A3.1.1 Short history
A3.1.2 Brief information about light and used light devices
A3.2 Description of innovation
A3.3 Theory of the multi-reflex engine
A3.4 Discussion
References
4 Optimal trajectories of air and space vehicles
Summary
Nomenclature (in metric system)
A4.1 Introduction
A4.2 General equations
A4.3 Flight with a small change of vehicle mass and flight path angle
A4.4 Statement of the problem
A4.4.1 Subsonic speed (V & 270 m/s) and different engines
A4.4.1.1 Aircraft with rocket engine
A4.4.1.2 Aircraft with turbo-jet engine
A4.4.1.3 Piston and turbo engines with propeller
A4.4.2 Hypersonic speed (1 km/s & V & 7 km/s)
A4.4.2.1 Rocket engine or hypersonic glider
A4.4.2.2 Ramjet engine
A4.5 Optimal wing area
A4.5.1 Subsonic speed
A4.5.2 Hypersonic speed
A4.6 Estimation of flight range
A4.6.1 Air and space vehicles without thrust
A4.6.2 Subsonic aircraft with thrust: horizontal flight
A4.7 Optimal engine control for constant flight pass angle
A4.8 Solution
A4.9 Simultaneous optimization of the path angle and fuel consumption
A4.10 Application to aircraft, rocket missiles, and cannon projectiles
A4.10.1 Application to rocket vehicles and missiles
A4.10.1.1 The optimal trajectory for a fixed wing space vehicle
A4.10.1.2 Rockets, missiles and space vehicles with variable wings
A4.10.1.3 Increasing the rocket payload for the same range
A4.10.1.4 Conclusion
A4.10.2 Application to cannon wing projectiles
A4.10.2.1 Conclusion
A4.10.3 Application to current aircraft
A4.10.3.1 Conclusion
A4.11 General discussion and conclusion
References
5 High-efficiency transfer of mechanical energy
Summary
A5.1 Introduction
A5.2 Description of innovation
A5.3 Theory of air energy transfer (in metric system)
A5.4 Discussion
A5.4.1 Cable problem
A5.4.2 Building problems
A5.4.3 Air traffic problems
A5.5 Advantages of proposed method
A5.6 Defect
References
6 Optimal aircraft thrust angles
Summary
Nomenclature
A6.1 Introduction
A6.2 General methodology
A6.3 OTA for takeoff and landing
A6.4 Optimal angle of thrust vector in horizontal flight (cruise regime)
A6.5 Climb and descent regimes
A6.6 Turning of airplane
A6.7 Discussion
A6.8 Conclusions
References
Appendix 1 System of mechanical and electrical units and other useful values
1.1 System of mechanical and electrical units
1.2 Fundamental physical constants
1.3 Astronomical data
1.4 Density of gases at normal pressure and temperature 0°C in kg/m3
1.5 Parameters of earth atmosphere (relative density and temperature)
General references
Russian works
NIAC reports
Bolonkin's Papers are Presented in American Scientific Conferences 2006 or Accepted for Publications
Index

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