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.


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    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 :

    1973-05-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Solid Propellant Rocket Motor

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


    SOLID PROPELLANT ROCKET MOTOR

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



    Miniature solid propellant rocket motor

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


    A miniature solid propellant rocket motor

    Grubelich, M. / Hagan, M. / Mulligan, E. | AIAA | 1997