A supersonic combustion rocket is described in which large turbopumps for fuel and oxidizers are eliminated by the use of a small rocket motor upstream of the mixing chamber. The exhaust from the small rocket motor creates a pressure differential between the storage tanks for the fuel and oxidizers and the mixing chamber which causes the propellant components to flow from the tanks to the chamber. As the propellant passes between the storage tanks for the fuel and oxidizers and the mixing chamber which causes the propellant components to flow from the tanks to the chamber. As the propellant passes the small rocket motor, it becomes entrained in the exhaust gases and may enter the mixing chamber at supersonic speeds. The proposed system results in a rocket motor having substantially greater efficiency than a motor of the same size using a turbopump feed system.


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    Titel :

    Supersonic Combustion Rocket


    Beteiligte:
    R. J. Weber (Autor:in) / L. C. Franciscus (Autor:in)

    Erscheinungsdatum :

    1972


    Format / Umfang :

    8 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Supersonic-combustion rocket

    Weber, R. J. / Franciscus, L. C. | NTRS | 1973


    Supersonic-Combustion Rocket

    R. J. Weber / L. C. Franciscus | NTIS | 1973