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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    Titel :

    Space Shuttle Orbit Maneuvering Engine Reusable Thrust Chamber Program


    Beteiligte:
    J. M. Senneff (Autor:in)

    Erscheinungsdatum :

    1975


    Format / Umfang :

    74 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch