The feasibility of potential reusable thrust chamber concepts is studied. Propellant condidates were examined and analytically combined with potential cooling schemes. A data base of engine data which would assist in a configuration selection was produced. The data base verification was performed by the demonstration of a thrust chamber of a selected coolant scheme design. A full scale insulated columbium thrust chamber was used for propellant coolant configurations. Combustion stability of the injectors and a reduced size thrust chamber were experimentally verified as proof of concept demonstrations of the design and study results. (Author)


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    Title :

    Space Shuttle Orbit Maneuvering Engine Reusable Thrust Chamber Program


    Contributors:

    Publication date :

    1975


    Size :

    74 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English