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

    Publication date :

    1978-04-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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