Examination of range of missions and use of atmosphere braking; 2 modes are considered, Mars orbital rendezvous with landing to be accomplished by excursion vehicle detached from parent orbiting spacecraft, and direct landing of entire spacecraft on Mars; system weights are presented in terms of number of men in crew, trip time, and stay time on Mars; chemical and nuclear propulsion is considered; chemical system is hydrogen-fluorine system with specific impulse of 450 sec; nuclear system has specific impulse of 820 sec, ratio of thrust-to-engine weight of 12, and for orbital operations thrust-to-gross weight ratio of 0.3.


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    Titel :

    Preliminary study of spacecraft for manned Mars orbiting and landing missions


    Weitere Titelangaben:

    SAE -- Paper


    Beteiligte:
    Wong, T.J. (Autor:in) / Anderson, J.A. (Autor:in)

    Kongress:

    SAE Meeting ; 1964 Interplanetary



    Erscheinungsdatum :

    1964


    Format / Umfang :

    11 pages


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    A Preliminary Study of Spacecraft for Manned Mars Orbiting and Landing Missions

    Anderson, Joseph L. / Wong, Thomas J. | SAE Technical Papers | 1964


    Manned Mars landing missions using electric propulsion

    Fishbach, L. H. / Hrach, F. J. / Mac Kay, J. S. et al. | NTRS | 1966



    Manned MARS Landing Missions Using Electric Propulsion

    L. H. Fishbach / F. J. Hrach / J. S. Mac Kay et al. | NTIS | 1966