Space Transport and Engineering Methods/Ion and Plasma Engines

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D.6 Ion and Plasma Engines

Contents 1 arc jet 2 electrostatic ion 3 solar-electric ion 4 thermoelectric ion 5 laser-electric ion 6 microwave-electic ion 7 nuclear-electric ion 8 electron beam heated plasma 9 microwave heated plasma 10 fusion heated plasma 11 antimatter-heated plasma 12 further reading

[edit] arc jet

48 Arc Jet

Alternate Names:

Type:

Description:

Sunlight is converted to electricity by a photovoltaic array. The electricity

is arced through a propellant stream, heating it. The propellant is then

expanded through a nozzle.

Status:

Variations:

References:

[D34] Hardy, Terry L.; Curran, Francis M. "Low Power DC Arcjet

Operation with Hydrogen/Nitrogen/Ammoinia Mixtures", NASA

Technical Memorandum 89876, 1987.

[D35] Stone, James R.; Huston, Edward S. "NASA/USAF Arcjet

Research and Technology Program", NASA Technical Memorandum

100112, 1987.

[D36] Kagaya, Y. et al "Quasi-steady MPD Arc-jet for Space

Propulsion", Symposium for Space Technology and Science, Tokyo,

Japan, 19 May 1986, pp 145-154, 1986.

[D37] Manago, Masata et al "Fast Acting Valve for MPD Arcjet", IHI

Engineering Review, v 19 no 2 pp 99-100, April 1986.Ê Ê

[D38] Pivirotto, T. J.; King, D. Q. "Thermal Arcjet Technology for

Space Propulsion", Chemical Propulsion Information Agency, Laurel,

Maryland, 1985.

[edit] electrostatic ion

49 Electrostatic Ion

Alternate Names:

Type:

Description:

Status:

Variations:

References:

[D39] Rawlin, Vincent K; Patterson, Michael J. "High Power Ion Thruster

Performance", NASA Technical Memorandum 100127, 1987.

[edit] solar-electric ion

49a Solar-Electric Ion

Sunlight is converted to electricity by a photovoltaic array. The electricity

is used to ionize and electrostatically accelerate the propellant.

[D40] Mitterauer, J. "Liquid Metal Ion Sources as Thrusters for Electric

Space Propulsion", J. Phys. Colloq. (France) vol 48, no C-6, pp 171-6,

Nov. 1987.

[D41] Mitterauer, J. "Field Emission Electric Propulsion - Emission Site

Distribution of Slit Emitters", IEEE Trans. on Plasma Sci. vol PS-15, pp

593-8, Oct. 1987.

[D42] Stuhlinger, E. et al "Solar-Electric Propulsion for a Comet Nucleus

Sample Return Mission" presented at 38th Congress of the

International Astronautical Federation, Brighton, England, 10 Ocotober

1987.

[D43] Nakamura, Y.; Kuricki, K. "Electric Propulsion Test Onboard the

Space Station", Space Solar Power Review vol 5 no 2 pp 213-9, 1985.

[D44] Voulelikas, G. D. "Electric Propulsion: A Review of Future Space

Propulsion Technology" Communications Research Centre, Ottawa,

Ontario, report number CRC-396, October 1985.

[Dnn] Bartoli, C. et al

"A Liquid Caesium Field Ion Source for Space Propulsion", J. Phys. D vol

17 no 12 pp 2473-83, 14 Dec. 1984.

[D45] Imai, R.; Kitamura, S. "Space Operation of Engineering Test

Satellite -III Ion Engine", Proceedings of JSASS/AIAA/DGLR 17th Intl.

Electric Propulsion Conf. pp 103-8, 1984.

[D46] Jones, R. M.; Poeschel, R. L. "Primary Space Propulsion for 1995-

2000 - Electrostatic Technology Applications" AIAA/SAE/ASME 20th Joint

Propulsion Conference, AIAA paper number 84-1450, 1984.

[D47] Bartoli, C. et al "Recent Developments in High Current Liquid

Metal Ion Sources for Space Propulsion", Vacuum vol 34 no 1-2 pp 43-6,

Jan. -Feb. 1984.

[D48] Brophy, J. R.; Wilbur, P. J. "Recent Developments in Ion Sources

for Space Propulsion", Proceedings of the Intl. Ion Engineering Congress

vol 1 pp 411-22, 1983.

[Dnn] Anon. "Ion Propulsion Engine Tests

Scheduled", Aviation Week and Space Technology, v 116 no 26 pp 144-5,

1982.

[D49] James, E.; Ramsey, W., Sr.; Steiner, G. "Developing a Scaleable

Inert Gas Ion Thruster", AIAA paper number 82-1275 presented at

AIAA/SAE/ASME 18th Joint Propulsion Conference, Cleveland, OH, 21-

23 June 1982.

[D50] Zafran, S. et al "Aerospace Highlights 1982: Electric

Propulsion", Astronautics and Aeronautics, v 20 no 12 pp 71-72, 1982.

[D51] Clark, K. E.; Kaufman, H. B. "Aerospace Highlights 1981: Electric

Propulsion", Astronautics and Aeronautics, v 19 no 12 pp 58-59, 1981.

[D52] Kaufman, H. R. "Performance of Large Inert-Gas Thrusters",

AIAA paper number 81-0720 presented at 15th International Electric

Propulsion Conference, Las Vegas, Nevada, 21-23 April 1981.

[D53] Byers, D. C.; Rawlin, V. K. "Critical Elements of Electron-

Bombardment Propulsion for Large Space Systems", J. Spacecraft and

RocketsÊ vol 14 no 11 pp 648-54, Nov. 1977.

[D55] Mutin, J.; Tatry, B. "Electric Propulsion in the Field of Space",

Acta Electron. (France) vol 17 no 4 pp 357-70, Oct. 1974 (in French).

[edit] thermoelectric ion

49b Thermoelectric Ion

Radioactive isotope decay produces heat. Heat is converted to electricity by

semiconductors. Electricity ionizes and accelerates atoms in engine.Ê

[edit] laser-electric ion

49c Laser-Electric Ion

Laser tuned to optimum absorption wavelength of photovoltaic cells. Cells

convert laser light to electricity, which is used to power ion engine. Ion

engine accelerates ionized propellants electrostatically.

[D56] Maeno, K. "Advanced Scheme of CO2 Laser for Space

Propulsion", Space Solar Power Review vol 5 no 2 pp 207-11, 1985.

[edit] microwave-electic ion

49d Microwave-Electric Ion

A microwave receiving antenna (rectenna) on spacecraft converts

microwaves to electricity. Electricity is used to ionize and accelerate

atoms.

[D57] Nordley, G. D.; Brown, W. C. "Space Based Nuclear-Microwave

Electric Propulsion", 3rd Symposium on Space Nuclear Power Systems,

Albuquerque, New Mexico, 13 January 1986, pp 383-95, 1987.

[edit] nuclear-electric ion

49e Nuclear-Electric Ion

Nuclear reactor generates heat, which is converted to electricity in

thermoelectric or turbine/generator cycles. Electricity is used to ionize

propellant and accelerate it by electrostatic voltage.

[D58] Cutler, A. H. "Power Demands for Space Resource Utilization",

Space Nuclear Power Systems 1986 pp 25-42.

[D59] Buden, D.; Garrison, P. W. "Space Nuclear Power Systems and

the Design of the Nuclear Electric Propulsion OTV", presented at

AIAA/SAE/ASME 20th Joint Propulsion Conference, AIAA paper number

84-1447, 1984.

[D60] Powell, J. R.; Boots, T. E. "Integrated Nuclear Propulsion/Prime

Power Systems", AIAA paper number 82-1215 presented at

AIAA/SAE/ASME 18th Joint Propulsion Conference, Cleveland, Ohio,

21-23 June 1982.

[D61] Powell, J. R.; Botts, T. E.; Myrabo, L. N. "Annular Bed Nuclear

Power Source for Electric Thrusters", AIAA paper number 82-1278

presented at AIAA/SAE/ ASME 18th Joint Propulsion Conference,

Cleveland, Ohio, 21-23 June 1982.

[D62] Ray, P. K. "Solar Electric versus Nuclear Electric Propulsion in

Geocentric Space", Trans. Am. Nucl. Soc. vol 39 pp 358-9, Nov.-Dec.

1981.

[D63] Hsieh, T. M.; Phillips, W. M. "An Improved Thermionic Power

Conversion System for Space Propulsion", Proceedings of the 13th

Intersociety Energy Conversion Engineering Conference pp 1917-1923,

1978.

[D64] Reichel, R. H. "The Air-Scooping Nuclear-Electric Propulsion

Concept for Advanced Orbital Space Transportation Missions", J. British

Interplanetary Soc. vol 31 no 2 pp 62-6, Feb. 1978.

[edit] electron beam heated plasma

50 Electron Beam Heated Plasma

Alternate Names:

Type:

Description: A high voltage (hundreds of keV) electron beam is injected

axially into a propellant flow. The electron beam heats the flow to plasma

temperatures, which produces high specific impulse. Cool gas is injected

along the chamber walls to provide film cooling and protect the chamber

from the very high temperature plasma.

Status:

Variations:

References:

[edit] microwave heated plasma

51 Microwave Heated Plasma

Alternate Names: Electron-Cyclotron Absorption Rocket

Type:

Description:Ê Partially ionized gas directly absorbs microwaves,

becomingÊhot, then expands through rocket nozzle.

Status:

Variations:

References:

[edit] fusion heated plasma

52 Fusion Heated Plasma

Alternate Names:

Type:

Description: Exhaust of pure fusion rocket is a thin, extremely hot

plasma. If higher thrust is needed, hydrogen can be mixed with plasma.

This increases thrust at the expense of performance.

Status:

Variations:

References:

52a Reactor leakage mixed

52b Plasma Kernal Mixed

[edit] antimatter-heated plasma

53 Antimatter-Heated Plasma

Alternate Names:

Type:

Description: Exhaust of pure antimatter rocket is a charged particles. If

higher thrust is needed, hydrogen can be mixed with plasma. This

increases thrust at the expense of performance.

Status:

Variations:

References:

[edit] further reading

• Wikipedia: plasma propulsion engine