In design study of modularized electric-propulsion system adaptable to several planetary missions, two spacecraft designs were derived; one, sized for Titan III-M could perform Mars orbiter/lander missions during 1971 to 1979 launch opportunities; second, sized for SLV-3C/Centaur, could perform Jupiter flyby mission; based on optimum design points, 9.6-kw system for Mars orbiter, and 17-kw system for Jupiter flyby spacecraft were designed; these ion-engine systems, consisting of thruster arrays, storage and feed systems, and powerconditioning and control systems, are designed to satisfy requirements of mission, reliability, solar power source, and spacecraft integration; designs were based on state-of-art mercury-bombardment ion thrusters. (17791)


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    Title :

    Solar-electric propulsion systems for unmanned space missions


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Molitor, J.H. (author) / Olson, R.N. (author)

    Published in:

    Publication date :

    1968


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    Solar-electric-propulsion systems for unmanned space missions.

    Molitor, J. H. / Olson, R. N. | NTRS | 1968


    Solar-electric propulsion systems for unmanned space missions.

    Molitor, J. H. / Olson, R. N. | NTRS | 1967



    Minimum-time space missions with solar electric propulsion

    Quarta, Alessandro A. | Online Contents | 2011