Objective of design study was to show feasibility of system; to uncover specific problem areas, Mars orbiter mission utilizing Saturn IB/Centaur boost vehicle was chosen as mission model; design constraints evaluated include requirements of mission, interface problems between spacecraft and propulsion system, and characteristics of state-of-art ion engine subsystems; that is, thruster, feed system, power conditioning, and controls; conceptual design of 48-kw-propulsion system is developed.


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    Title :

    Design of solar-electric propulsion system for interplanetary spacecraft


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Molitor, J.H. (author) / Berman, D. (author) / Seliger, R.L. (author) / Olson, R.N. (author)

    Published in:

    Publication date :

    1967


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Interplanetary spacecraft design using solar electric propulsion

    Duxbury, J. / Paul, G. | Tema Archive | 1974




    Interplanetary Spacecraft Design using Solar Electric Propulsion

    John H. Buxbury / Gary M. Paul | AIAA | 1976


    Design of a solar-electric propulsion system for interplanetary spacecraft

    BERMAN, D. / MOLITOR, J. / OLSON, R. et al. | AIAA | 1966