The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Solid propellant rocket motor


    Beteiligte:
    Dowler, W. L. (Autor:in) / Shafer, J. I. (Autor:in) / Behm, J. W. (Autor:in) / Strand, L. D. (Autor:in)

    Erscheinungsdatum :

    01.05.1973


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    SOLID PROPELLANT ROCKET MOTOR

    W. L. Dowler / J. I. Shafer / J. W. Behm et al. | NTIS | 1971


    Solid Propellant Rocket Motor

    W. L. Dowler / J. I. Shafer / J. W. Behm et al. | NTIS | 1973



    Miniature solid propellant rocket motor

    M. C. Grubelich / M. Hagan / E. Mulligan | NTIS | 1997


    Solid Propellant Rocket Motor Thermal Analysis

    Heatherly, E. R. / Gonzalez, J. I. | SAE Technical Papers | 1962