The completed phases of a study evaluating LOX/hydrocarbon auxiliary propulsion system concepts for a second generation Space Shuttle Orbital Maneuvering Subsystem (OMS) and Reaction Control Subsystem (RCS) are presented. The results of the preliminary system evaluation phase are summarized, and efforts regarding the in-depth system evaluation phase are described. Ethanol and methane are considered to be the best fuel candidates as both are non-coking, non-corrosive, and offer high performance capability. Ethanol affords the highest dV and total impulse capability because of its high density-specific impulse product, while methane affords the lowest system wet weight when the system is sized for a fixed dV or total impulse requirement. The LOX/ethanol system allows the use of a simple non-insulated RCS feed system, and is the most attractive LOX/hydrocarbon OMS-RCS. Its operational costs would be substantially less than the current N2O4/MMH system.


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    Title :

    LOX/hydrocarbon auxiliary propulsion for the Space Shuttle Orbiter


    Contributors:
    Orton, G. F. (author) / Mark, T. D. (author)

    Conference:

    Joint Propulsion Conference ; 1982 ; Cleveland, OH


    Publication date :

    1982-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    LOX/Hydrocarbon auxiliary propulsion for the Space Shuttle Orbiter

    ORTON, G. / MARK, T. / LAUSTEN, M. | AIAA | 1981


    LOX/Hydrocarbon auxiliary propulsion for the Space Shuttle Orbiter

    Orton, G. F. / Mark, T. D. / Lausten, M. F. | NTRS | 1981



    Auxiliary Propulsion Subsystems for the Space Shuttle Orbiter

    Jones, Donald L. | SAE Technical Papers | 1973