Results obtained with technique of obtaining thrust vector control by injection of various liquids into supersonic region of rocket nozzle; liquids studied were water, Freon-12, perchloroethylene, nitrogen tetroxide, and bromine; unsymmetrical dimethylhydrazine and inhibited red fuming nitric acid were injected simultaneously to explore effect of energy release in nozzle exit cone with bipropellant injection; data on relationships of side force to injectant flow rate, effect of axial location of injection port, pressure, and properties.


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    Title :

    Liquid injection thrust vector control


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 1 , n 3


    Publication date :

    1963


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Liquid-Injection Thrust Vector Control.

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    LIQUID INJECTION THRUST VECTOR CONTROL

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    Moment characteristics of liquid injection thrust vector control

    MASUYA, G. / CHINZEI, N. / ISH S. | AIAA | 1976


    Thrust vector control by reactive liquid secondary injection

    Fox, J. J. / Fukumoto, A. / Sedgley, D. W. | NTRS | 1962