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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    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