A concept for a near-term multi-stage space launch system has been proposed. The configuration incorporated full reusability, horizontal take-off and landing characteristics, and a payload goal of 50,000 lbs into a 100 n mi circular airbreathing propulsion system, augmented by conventional rocket propulsion as required. The second stage (orbiter) featured a high lift-to-drag ratio aerodynamic design with a dedicated high volume payload bay. Propulsion for the second stage was provided by a conventional rocket engine. The orbiter component was carried nestled within the booster mold lines and staged through a bottom drop mode. Sensitivity studies were performed on the synergisms between elements of the boost propulsion system; dynamic pressure effects on system performance; degraded ramjet thrust at high Mach numbers; and booster weight at staging. The configuration evolution and results from the sensitivity studies are described in detail.


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    Titel :

    Advanced Launch Vehicle Configurations and Performance Trades


    Beteiligte:
    P. R. Gord (Autor:in) / K. J. Langan (Autor:in) / M. E. Stringer (Autor:in)

    Erscheinungsdatum :

    1990


    Format / Umfang :

    13 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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