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A Nuclear-Thermionic-Ionic Propulsion System

  • J. E. Cobb
  • W. E. Cutler
  • A. F. Dugan
  • R. H. Olds
  • G. B. Shook
Conference paper

Abstract

An electrical propulsion system for space probe missions to remote points in the solar system is described and analyzed in regard to feasibility and capability. It combines a nuclear reactor heat source with thermionic electrical power generators to provide requisite power for a cesium ion rocket motor. By the use of static techniques for transport and conversion of energy, the design emphasizes the avoidance of mechanically moving parts as major links in the transfer of power from the nuclear reactor to the ion motor so as to achieve maximum reliability for prolonged unattended operation in space.

Keywords

Waste Heat Propulsion System Thermionic Generator Voltage Convertor Vacuum Diode 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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References

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    Schlichter, dissertation, University of Gottingen (1915).Google Scholar
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    Schnetzer, E., and Corliss, W., American Nuclear Society, Detroit meeting (December 1958).Google Scholar
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    Stuhlinger, E., Jour. Astronautics, 2, 149–152 (1955); 3, 33–36 (1956).Google Scholar
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    Stuhlinger, E., Jet Propulsion, 27, 410–414 (1957).CrossRefGoogle Scholar
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    Edwards, R., General Electric Corp., Cincinnati, Ohio, oral communication to Lockheed Missiles and Space Division, Palo Alto, California (December 3, 1958 ).Google Scholar
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    Firsov, O. B., Jour. Exper. and Theo. Phys., 21, 1001–1008 (1951).Google Scholar

Copyright information

© Springer-Verlag Wien 1961

Authors and Affiliations

  • J. E. Cobb
    • 1
  • W. E. Cutler
    • 1
  • A. F. Dugan
    • 1
  • R. H. Olds
    • 1
  • G. B. Shook
    • 1
  1. 1.Lockheed Aircraft CorporationSunnyvaleUSA

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