Average burning rates of solid rocket propellants were measured in acceleration fields up to 2000 times standard acceleration of gravity; acceleration vector was perpendicular to and into burning surface; propellant strands were burned in combustion bomb mounted on centrifuge, and surge tanks were employed to insure constant pressure burning at 500, 1000, and 1500 psia; burning rates of aluminized and nonaluminized propellants were found to depend on acceleration; results are compared to analytical models proposed by C.T.Crowe for aluminized propellants and by R.L.Glick for nonaluminized propellants.


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    Title :

    Investigation of effect of acceleration on burning rate of composite propellants


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 6 , n 2


    Publication date :

    1968


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    Effect of acceleration on the burning rate of composite propellants

    CAVENY, L. / GLICK, R. / HODGE, B. | AIAA | 1967


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    Caveny, L. H. / Glick, R. L. / Hodge, B. K. | NTRS | 1967




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