The suitability of the baseline 30 cm thruster for future space missions was examined. Preliminary design concepts for several advanced thrusters were developed to assess the potential practical difficulties of a new design. Useful methodologies were produced for assessing both planetary and earth orbit missions. Payload performance as a function of propulsion system technology level and cost sensitivity to propulsion system technology level are among the topics assessed. A 50 cm diameter thruster designed to operate with a beam voltage of about 2400 V is suggested to satisfy most of the requirements of future space missions.


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    Titel :

    Advanced Electrostatic Ion Thruster for Space Propulsion


    Beteiligte:
    T. D. Masek (Autor:in) / D. Macpherson (Autor:in) / W. Gelon (Autor:in) / S. Kami (Autor:in) / R. L. Poeschel (Autor:in)

    Erscheinungsdatum :

    1978


    Format / Umfang :

    400 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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