A computerized preliminary design system is used to evaluate potential main liquid-rocket propulsion systems for advanced technology winged single-stage-to-orbit launch vehicles. Evaluated are trade-offs between ascent flight trajectory performance and flight vehicle sizing driven by engine mass and propellant requirements. Numerous mission, flight, and vehicle-related requirements and constraints are satisfied in the design process. With the design system, five dual-mode propulsion system concepts are compared to a baseline hydrogen and oxygen system in terms of the changes in vehicle dry mass and gross mass.


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    Title :

    Optimization and evaluation of main liquid rocket propulsion systems for advanced earth-to-orbit shuttles


    Contributors:

    Conference:

    Joint Propulsion Conference ; 1978 ; Las Vegas, NV, US


    Publication date :

    1978-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English