Under a 1-year funded by the International Telecommunication Satellite Organization, the Rocketdyne Division of Rockwell International designed, fabricated, and tested a full-scale, advanced, storable, pressure-fed thruster for blowdown operation in the 1-lbf thrust range. The purpose of the program was a full-scale technology demonstration of an engine appropriate for use as a satellite station-keeping and attitude-control thruster. The primary features of the thruster are high performance, reduced plume contaminant production, and long life. Using nitrogen tetroxide and monomethyl-hydrazine, the thruster operates at 50 psia chamber pressure and produces a nominal vacuum specific impulse of 300 seconds with a 150:1 nozzle expansion ratio. The thruster chamber is made of beryllium and is radiation cooled. Reduction of the plume contaminant is accomplished by providing improved propellant evaporation for high combustion efficiency and by reduction of thruster propellant dribble volumes.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Minimizing Plume Contamination Production in Bipropellant Thrusters


    Contributors:

    Publication date :

    1984


    Size :

    9 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Investigation of the Contamination Properties of Bipropellant Thrusters

    Rebrov, S. / Gerasimov, Y. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2001



    International Space Station Bipropellant Plume Contamination Model

    Soares, Carlos / Mikatarian, Ronald / Barsamian, Hagop et al. | AIAA | 2002