Ion propulsion modules employing 8-cm thrusters and 30-cm thrusters were studied for Multimission Modular Spacecraft (MMS) applications. Recurring and nonrecurring cost elements were generated for these modules. As a result, ion propulsion cost drivers were identified to be Shuttle charges, solar array, power processing, and thruster costs. Cost effective design approaches included short length module configurations, array power sharing, operation at reduced thruster input power, simplified power processing units, and power processor output switching. The MMS mission model employed indicated that nonrecurring costs have to be shared with other programs unless the mission model grows. Extended performance missions exhibited the greatest benefits when compared with monopropellant hydrazine propulsion.


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    Title :

    Ion Propulsion Cost Effectivity


    Contributors:
    S. Zafran (author) / J. J. Biess (author)

    Publication date :

    1978


    Size :

    88 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Ion propulsion cost effectivity

    ZAFRAN, S. / BIESS, J. / CALLENS, R. | AIAA | 1979


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    Zafran, S. / Biess, J. J. | NTRS | 1978


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    Ion propulsion cost effectivity

    Zafran, S. / Biess, J. J. / Callens, R. A. | NTRS | 1979


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