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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    Title :

    Advanced Electrostatic Ion Thruster for Space Propulsion


    Contributors:
    T. D. Masek (author) / D. Macpherson (author) / W. Gelon (author) / S. Kami (author) / R. L. Poeschel (author)

    Publication date :

    1978


    Size :

    400 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Advanced electrostatic ion thruster for space propulsion

    Masek, T. D. / Macpherson, D. / Gelon, W. et al. | NTRS | 1978




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