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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Liquid injection thrust vector control


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Green, C.J. (Autor:in) / McCullough, Jr., F. (Autor:in)

    Erschienen in:

    AIAA Journal ; 1 , n 3


    Erscheinungsdatum :

    1963


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Liquid-Injection Thrust Vector Control.

    Richard J. Zeamer | AIAA | 1977


    LIQUID INJECTION THRUST VECTOR CONTROL

    GREEN, C. J. / MC CULLOUGH / F. | AIAA | 1963


    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