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Electric space propulsion systems

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Abstract

Active development of electric thrustors began 10 years ago. Today, several kinds of thrustors have achieved efficiencies above 90 % and lifetimes of several thousand hours. The following article derives the basic theory of electric thrust production at constant exhaust velocity, and at variable exhaust velocity programmed for optimum vehicle performance. Electrothermal or arcjet; electrostatic or ion; and electrodynamic or plasma thrustors are described. At the present time, ion thrustors of the electron bombardment and of the surface ionization types are the most promising systems. Electric power in space may be generated by solar cells or nuclear-electric generators. It is expected that the incore thermionic converter will eventually be the preferred system. A variety of missions with electric propulsion systems appear feasible and highly desirable, among them orbital station keeping, attitude control, planetary probes, solar and out-of-the-ecliptic probes, deep-space probes, and manned Mars and Venus exploration. For each mission, a careful systems-design study must be made, which will provide the optimum selection of thrustor type, thrust level, exhaust velocity, thrust program, power source, trajectory, and flight plan.

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Authors and Affiliations

  1. NASA-George C. Marshall Space Flight Center, Huntsville, Ala., USA

    Ernst Stuhlinger

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  1. Ernst Stuhlinger
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Stuhlinger, E. Electric space propulsion systems. Space Sci Rev 7, 795–847 (1967). https://doi.org/10.1007/BF00542896

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  • DOI: https://doi.org/10.1007/BF00542896

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