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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    Title :

    Preliminary study of spacecraft for manned Mars orbiting and landing missions


    Additional title:

    SAE -- Paper


    Contributors:
    Wong, T.J. (author) / Anderson, J.A. (author)

    Conference:

    SAE Meeting ; 1964 Interplanetary



    Publication date :

    1964


    Size :

    11 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :


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