A preliminary analysis has been made of a supersonic-combustion rocket engine concept using hydrogen and oxygen propellants. The ejector action of a separate small rocket motor is employed to pump the propellants to high stagnation pressures and supersonic velocities. Therefore complicated heavy turbopumps are eliminated and cooling problems of a sonic throat are reduced. The results of the study show that vacuum specific impulse levels as high as a conventional rocket having the same chamber pressure as the drive motor are possible. The supersonic-combustion rocket would be an attractive alternate for a high-altitude low-thrust conventional rocket operating with a pressure feed propellant system. It would also be a convenient technique for obtaining extremely high thrusts without the need for developing corresponding large turbopumps.


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    Titel :

    Analysis of a supersonic-combustion rocket concept


    Beteiligte:

    Erscheinungsdatum :

    01.02.1972


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Supersonic-Combustion Rocket

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


    Supersonic-combustion rocket

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


    Supersonic Combustion Rocket

    R. J. Weber / L. C. Franciscus | NTIS | 1972