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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Solar electric low-thrust Mercury orbiter missions.


    Beteiligte:
    Klopp, D. A. (Autor:in) / Wells, W. C. (Autor:in)

    Kongress:

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


    Erscheinungsdatum :

    1972-04-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Solar electric low-thrust Mercury orbiter missions

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


    Ballistic mode Mercury orbiter missions.

    Hollenbeck, G. R. | NTRS | 1973



    Ballistic mode Mercury orbiter missions

    HOLLENBECK, G. | AIAA | 1973