A case bonded end burning solid propellant rocket motor is described. A propellant with sufficiently low modulus to avoid chamber buckling on cooling from cure and sufficiently high elongation to sustain the stresses induced without cracking is used. The propellant is zone cured within the motor case at high pressures equal to or approaching the pressure at which the motor will operate during combustion. A solid propellant motor with a burning time long enough that its spacecraft would be limited to a maximum acceleration of less than 1 g is provided by one version of the case bonded end burning solid propellant motor of the invention.


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    Title :

    Solid Propellant Motor


    Contributors:
    J. I. Shafer (author) / H. E. Marsh (author)

    Publication date :

    1970


    Size :

    8 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Solid propellant motor

    Shafer, J. I. / Marsh, H. E., Jr. | NTRS | 1978


    Solid propellant rocket motor

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


    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