A theoretical and experimental study was made of solid rocket ignition for the purpose of obtaining igniter design criteria. Heat-transfer, ballistic, and ignition data were obtained by firing a rocket-type igniter, venting noncondensable products at an unsteady rate, into a small rocket. Measurements were made of igniter and rocket pressures, grain surface temperatures, and ignition times. In the tests, the heat fluxes ranged from 19 to 48 cal/sq. cm.-sec and ignition times from .002 to .015 sec. It was found that the ignition test data were in fair agreement to those predicted from the von Elbe ignition theory. An igniter design method, developed from test data and the von Elbe theory, is described. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Solid-Propellant Rocket Ignition Research


    Contributors:

    Publication date :

    1964


    Size :

    2 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English







    Ignition-Transient Modeling for Solid Propellant Rocket Motors

    Alavilli, P. / Buckmaster, J. / Jackson, T. L. et al. | British Library Conference Proceedings | 2000


    The ignition transient in solid propellant rocket motors

    PARKER, K. / SUMMERFIELD, M. | AIAA | 1964