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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Minimizing Plume Contamination Production in Bipropellant Thrusters


    Beteiligte:
    E. A. DeGaetano (Autor:in) / W. T. Webber (Autor:in)

    Erscheinungsdatum :

    1984


    Format / Umfang :

    9 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    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