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

    Publication date :

    1973-05-01


    Type of media :

    Miscellaneous


    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

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



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    Solid Propellant Rocket Motor Thermal Analysis

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