Results of a preliminary study of unmanned Mercury orbiter missions which might be flown in the early 1980s. Five different levels of orbiter size and complexity are considered, ranging from a small orbiter carrying 22 kg of low data-rate instruments to a dual satellite mission employing 110 kg of science instruments emphasizing regional and local scale surface imagery. An Intermediate-20 class launch vehicle is required to deliver a minimal surface-imaging science package into Mercury orbit using a ballistic mission mode. Employment of a 15 kW solar electric low-thrust stage permits delivery of the more capable dual satellite package with a Titan IIID (5)/Centaur.


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    Title :

    Solar electric low-thrust Mercury orbiter missions.


    Contributors:
    Klopp, D. A. (author) / Wells, W. C. (author)

    Conference:

    American Institute of Aeronautics and Astronautics, Electric Propulsion Conference ; 1972 ; Bethesda, MD


    Publication date :

    1972-04-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Solar electric low-thrust Mercury orbiter missions

    KLOPP, D. / WELLS, W. | AIAA | 1972



    Ballistic mode Mercury orbiter missions

    HOLLENBECK, G. | AIAA | 1973


    Ballistic mode Mercury orbiter missions.

    Hollenbeck, G. R. | NTRS | 1973