A prototype 25 lb sub f gaseous oxygen/gaseous hydrogen thruster for Space Station propulsion application was designed and fabricated by Rocketdyne and endurance tested at the NASA/Marshall space Flight Center. The thruster incorporates a regeneratively cooled thrust chamber with a nozzle exit area ratio of 30, a 12-element coaxial injector, a spark igniter, and close-coupled propellant valves. Test results indicate that all major technology issues for long-life gaseous oxygen/gaseous hydrogen thrusters for Space Station application have been resolved.


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    Titel :

    A 25-LBF gaseous oxygen/gaseous hydrogen thruster for space station application


    Beteiligte:
    Heckert, B. J. (Autor:in) / Yu, T. I. (Autor:in) / Allums, S. L. (Autor:in) / Carrasquillo, E. A. (Autor:in)


    Erscheinungsdatum :

    01.08.1986


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch