A computerized preliminary design procedure has been used to determine rocket-engine bell-nozzle configurations which achieve either minimum gross mass or minimum dry mass on an advanced technology winged single-stage-to-orbit launch vehicle. This procedure evaluates the trade offs between the optimized ascent flight trajectory performance and the flight vehicle sizing driven by the engine mass and propellant requirements. Numerous mission, flight, and vehicle related requirements and constraints are satisfied in this process. Propulsion system configurations which incorporate dual-position nozzles are evaluated and compared to configurations using all fixed nozzles.


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    Title :

    Nozzle selection for optimized single-stage shuttles


    Contributors:

    Conference:

    International Astronautical Congress ; 1976 ; Anaheim, CA


    Publication date :

    1976-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Dual-fuel engine for single-stage shuttles

    BEICHEL, R. / OBRIEN, C. | AIAA | 1975


    Shuttles

    Driver, B. / Institution of Civil Engineers | British Library Conference Proceedings | 1996