Status of Electric Propulsion Systems for Space Missions

  • W. E. Moeckel
Conference paper
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 6)

Abstract

During the past few years, electric propulsion systems have passed from the status of ideas which look interesting but somewhat academic to the status of active research and development, with a firm and growing place in the nation’s space program. How has this come about, and is it really justifiable? The electric propulsion cycle itself looks tremendously cumbersome and roundabout — nuclear or solar energy is first converted to heat, which in turn is converted into electrical energy, which is used, either directly or indirectly, to accelerate the propellant rearward to produce thrust. In each portion of this cycle there are inefficiencies and technological difficulties which are far from negligible. Furthermore, electric propulsion systems are so heavy, relative to the thrust that they can produce, that they must be boosted into orbit before they can be used, and they are almost painfully slow in getting in and out of planetary gravitational fields.

Keywords

Electric Propulsion Specific Impulse Electric Power Supply Thrust Generator Electric Propulsion System 
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

  1. 1.
    W. E. Moeckel, “Propulsion Methods in Asttonautics,” Int. Series on Aeroscience and Space Flight, Vol. 2, pp, 1078–1097, Pergamon Press, New York (1959).Google Scholar
  2. 2.
    J. H. Irving and E. K. Blum, “Comparative Performance of Ballistic and Low-Thrust Vehicles for Flight to Mars,” Vistas in Astronautics, Vol. II, pp. 191–218, Pergamon Press, New York (1959).Google Scholar
  3. 3.
    W.E. Moeckel, “Fast Intexplanetary Trajectories with Low-Thrust Propulsion Systems,” NASA TO R-79 (1960).Google Scholar
  4. 4.
    W.E. Moeckel, L.V. Baldwin, R.E. English, B. Lubarsky and S.H. Masien, “Satellite and Space Propulsion Systems,” NASA TO D-285 (June, 1960).Google Scholar
  5. 5.
    S. H. Maslen, “Fusion for Space Propulsion,” IRE Transactions on Military Electronics, Vol. MIL-3, No. 2 (April, 1959),Google Scholar
  6. 6.
    W.E. Moeckel and W.D. Rayle, “NASA Research on Plasma Accelerators,” ARS 14th Annual Meering, Preprint No. 1005–59, Washington. (Nov. 16–20, 1959).Google Scholar
  7. 7.
    R.E. English, H. O. Slone, D.T. Bernatowicz, E.H. Davison and S. Lieblein, “A 20,000 Kilowatt Nuclear Turboeiectric Power Supply for Manned Space Vehicles,” NASA MEMO 2–20–59E (March, 1959).Google Scholar
  8. 8.
    J.C. E ward, “Electric Space Propulsion,” journal of Electrical Engineers, Vol. 79, No, 7 (July, 1960).Google Scholar
  9. 9.
    R. C. Weatherston and W.E. Smith, “A Method for Heat Rejection from Space Power plants,” ARS journal, Vol. 30, No. 3, pp, 268–269, (March, 1960).Google Scholar
  10. 10.
    J. Kaye and J. A. Welsh, Direct Conversion of Heat to Electricity, John. Wiley & Sons, New York (1960),Google Scholar
  11. 11.
    J. H. Childs and W. R. Mickelsen, “Grid Electrode Ion Rockets for Low Specific Impulse Missions,” presented at 2nd AFOSR Symposium on Advanced Propulsion Concepts, Boston, Mass. (Oct. 7–9, 1959).Google Scholar
  12. 12.
    H. Shelton and J. M. Sellen, “Neutralization Experiments on Broad Cesium Ion Beams,” ARS Semi-Annual Mtg., Preprint No. 1161–60, Los Angeles, Calif. (May 9–12, 1960).Google Scholar
  13. 13.
    H. Mirels and B. Rosenbaum, “Analysis of One-Dimensional Ion Rocket with Grid Neutralization,” NASA TN D-266 (1960).Google Scholar
  14. 14.
    E. E. Dangle and D. L. Lockwood, “NASA Experimental Research with ion Rockets,” ARS Semi-Annual Mtg., Preprint No. 1126–60, Los Angeles, Calif, (May 9–12, 1960).Google Scholar
  15. 15.
    W. R. Mickelsen and J. H. Childs, “Theoretical Analysis of Ultrahigh Vacuum Condensers.” Rev. Scient. Inst., Vol. 29, pp. 871–873 (1958).CrossRefGoogle Scholar
  16. 16.
    W. E. Moeckel, “Trajectories with Constant Tangential Thrust in Central Gravitational Melds,” NASA TN D-281 (1960).Google Scholar
  17. 17.
    J. F. Dugan Jr., “Analysis of Trajectory Parameters for Probe and Round-Trip Missions to Mars,” NASA TN D-281 (1960).Google Scholar

Copyright information

© Springer Science+Business Media New York 1961

Authors and Affiliations

  • W. E. Moeckel
    • 1
  1. 1.Lewis Research CenterNational Aeronautics and Space AdministrationClevelandUSA

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