When pulsing rocket engines are tested under altitude conditions, data show that probability of large ignition overpressures generally decreases as temperature of rocket engine increases; this trend suggests that large ignition overpressures are related to accumulations of energy-rich substances on internal surfaces of engine; analytical and experimental investigation of this hypothesis and of means for insuring smooth ignition of pulsing rocket engines are presented; results show that large ignition overpressures can be avoided if engine walls are kept warm enough to prevent residual materials from accumulating in combustion chamber during duty cycles being fired.


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    Title :

    Ignition transients in small hypergolic rockets


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Juran, W. (author) / Stechman, R.C. (author)

    Published in:

    Publication date :

    1968


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Ignition transients in small hypergolic rockets.

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