Interim results of feasibility study presented include analytical tool for simultaneously optimizing vehicle design and its associated trajectory, typical resultant vehicle-trajectory concept, and preliminary parametric performance data; straightforward vehicle design using standard Saturn V launch vehicles is reasonably feasible; required initial mass in Earth orbit lies between 400,000 and 900,000 kg, depending on trip time, Earth return conditions, and power plant specific weight; electrical power of 3 to 8 Mw is required at power plant specific weight of 10 to 20 kg/kw.


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    Title :

    Application of nuclear electric propulsion to manned Mars missions


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Brown, H. (author) / Coates, G.L. (author)

    Published in:

    Publication date :

    1966


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




    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