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

    Erscheinungsdatum :

    01.04.1978


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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