Study made to determine performance characteristics of systems in thrust range required for attitude control systems; characteristic exhaust velocities for hydrazine and nitrogen tetroxide were measured with triplet and 2-on-2 injectors in 50 lb thrust uncooled combustion chamber at chamber pressure of 10 psia; steady state performance for oxidant fuel mixture ratios from 0.7 to 1.2; peak characteristic exhaust velocity was 5280 fps or 92% of theoretical value.


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    Titel :

    Performance of low-thrust storable-bipropellant rocket at very low chamber pressure


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:
    Wanhainen, J.P. (Autor:in) / DeWitt, R.L. (Autor:in) / Ross, P.S. (Autor:in)


    Erscheinungsdatum :

    1961


    Format / Umfang :

    22 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Performance of a low-thrust storable-bipropellant rocket at very low chamber pressure

    Wanhainen, John P. / DeWitt, Richard L. / Ross, Phil S. | TIBKAT | 1961


    Combustion instability in small earth storable bipropellant rocket engines

    CRONE, CHET / STECHMAN, CARL / WOLL, PETE | AIAA | 1993


    Thrust Prediction Model for Varying Chamber Pressure for a Hypergolic Bipropellant Liquid Rocket Engine

    Arun Kumar, P. / Rajeev Senan, C. / Ajith, B. et al. | Springer Verlag | 2018