The low pressure deflagration limit of controllable solid rocket propellants was experimentally investigated using low pressure combustion chambers and micro video recorders. The deflagration limit is affected by the specimen size, and this scale effect is explained by heat losses from the burning propellant to the surroundings. The effect of compositional variables of the propellant on subatmospheric combustion and the deflagration limit were studied. The variables were oxidizer blend ratio, binder types, oxidizer-fuel mixture ratio, aluminum content, mean particle diameter of the oxidizers and the size of aluminum powders. (Author)


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    Title :

    Low-Pressure Deflagration Limit of Controllable Solid Rocket Propellants


    Contributors:
    T. Godai (author) / M. Shimizu (author) / K. Ito (author) / H. Nishimura (author) / T. Tanemura (author)

    Publication date :

    1973


    Size :

    17 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Control of pressure deflagration limits of composite solid propellants

    Peterson, J.A. / Reed, Jr., R. / McDonald, A.J. | Engineering Index Backfile | 1967


    Control of pressure deflagration limits of composite solid propellants

    MCDONALD, A. / PETERSON, J. / REED, JR., R. | AIAA | 1966



    SOLID ROCKET PROPELLANTS

    Mama, Horrrluz P. | Online Contents | 1996