A space launcher that is recoverable was studied. Possible configurations were investigated and dimensioning parameters were identified. Analysis centered on design of a two-stage vehicle in a winged or ballistic configuration. The launch vehicle mission was defined as injection into low Earth orbit of a 10,000 kg payload. Results concern choice of propulsion system as well as ascent and descent trajectories (including implications for thermal protection).


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    Title :

    Future Launching Systems


    Contributors:
    M. Villain (author)

    Publication date :

    1981


    Size :

    71 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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