Using hypothesis that low frequency oscillations (chugging) in rocket engines, are result of oscillatory propellant flow induced by combustion time lag, conditions for suppression of such oscillations are derived; stability can be achieved by increases in length of feed line, velocity of propellant in feed line, ratio of feed pressure to chamber pressure, and ratio of chamber volume to nozzle area.


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    Title :

    Theory of unstable combustion in liquid propellant rocket systems


    Additional title:

    Am Rocket Soc -- J


    Contributors:

    Published in:

    Publication date :

    1951


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English