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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    Title :

    Solid Propellant Rocket Motor


    Contributors:
    W. L. Dowler (author) / J. I. Shafer (author) / J. W. Behm (author) / L. D. Strand (author)

    Publication date :

    1973


    Size :

    7 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    SOLID PROPELLANT ROCKET MOTOR

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


    Solid propellant rocket motor

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



    Miniature solid propellant rocket motor

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


    Spherical solid-propellant rocket motor Patent

    Styles, C. M. / Swain, R. L. / Thibodaux, J. G., Jr. | NTRS | 1961