A space simulation procedure was developed for studying rocket plume contamination effects using a 5-pound bipropellant reaction control system thruster. Vacuum chamber pressures of 3 x 10 to the minus 5 torr (70 miles altitude) were achieved with the thruster firing in pulse trains consisting of eight pulses (50 msec on, 100 msec off, and seven minutes between pulse trains). The final vacuum was achieved by cooling all vacuum chamber surfaces to liquid helium temperature and by introducing a continuous argon leak of 48 std. cc/sec into the test chamber. An effort was made to simulate propellant system flow dynamics corresponding to actual spacecraft mission use. Fast time response liquid flow rate measurements showed that large variations occurred in the ratio of oxidizer to fuel flow for pulse-on times up to 120 msec. These variations could lead to poor combustion efficiency and the production of contamination.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Space simulation experiments on reaction control system thruster plumes


    Beteiligte:
    Cassidy, J. F. (Autor:in)

    Kongress:

    Eurocon Computer Appl. Conf. ; 1972 ; New Orleans, United States


    Erscheinungsdatum :

    1972-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Visible spectra of thruster plumes from the Space Shuttle primary reaction control system

    Viereck, Rodney A. / Bernstein, Lawrence S. / Mende, Stephen B. et al. | AIAA | 1993



    Modeling ion thruster plumes

    Wang, J / Brophy, J / Liewer, P et al. | AIAA | 1995


    Electromagnetic wave scattering experiments in Hall thruster plasma plumes

    Gilchrist, Brian / Davis, Christopher / Carlson, Douglas et al. | AIAA | 1998