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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    Title :

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


    Contributors:


    Publication date :

    1986-08-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English