Results from a continuing, time-accurate computational study of the combustion gas flow inside the Space Shuttle Redesigned Solid Rocket Motor (RSRM) are presented. These computational fluid dynamic (CFD) analyses duplicate unsteady flow effects which interact in the RSRM to produce pressure oscillations, and resulting thrust oscillations, at nominally 15, 30, and 45 Hz. Results of the Navier-Stokes computations made at mean pressure and flow conditions corresponding to 80 seconds after motor ignition both with and without a protruding, rigid inhibitor at the forward joint cavity are presented here.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    A comparative study of the effects of inhibitor stub length on solid rocket motor combustion chamber pressure oscillations: RSRM at T = 80 seconds, preliminary results


    Beteiligte:
    Chasman, D. (Autor:in) / Burnette, D. (Autor:in) / Holt, J. (Autor:in) / Farr, R. (Autor:in)


    Erscheinungsdatum :

    01.07.1992


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch





    RSRM Chamber Pressure Oscillations: Transit Time Models and Unsteady CFD

    Nesman, T. / Stewart, E. / United States; National Aeronautics and Space Administration | British Library Conference Proceedings | 1996


    Analyses of Noise from Reusable Solid Rocket Motor (RSRM) Firings

    K. L. Gee / R. J. Kenny / T. W. Jerome et al. | NTIS | 2012


    Analyses of Noise from Reusable Solid Rocket Motor (RSRM) Firings

    Gee, Kent L. / Kenny, R. Jeremy / Jerome, Trevor W. et al. | NTRS | 2012


    Solid Rocket Motor Combustion Chamber Aeroacoustics

    Warren C. Strahle / John C. Handley | AIAA | 1978