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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Additional title:

    NASA -- Tech Note


    Contributors:
    Wanhainen, J.P. (author) / DeWitt, R.L. (author) / Ross, P.S. (author)


    Publication date :

    1961


    Size :

    22 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English




    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