In liquid injection thrust vector control, a rocket jet is deflected for steering purposed by injecting a liquid into the nozzle exit cone. The liquid is preferably both dense and reactive so that it adds mass and energy and generates shocks in the supersonic exhaust. This behavior increases thrust in the affected part of the jet producing not only a side force for steering but an addition to axial thrust. This paper presents a summary of current liquid injection thrust vector control technology, including procedures for design, development, analysis, testing and evaluation, together with supporting data and references.


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    Titel :

    Thrust vector control by liquid injection for solid propellant rockets


    Beteiligte:
    Zeamer, R. J. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference ; 1975 ; Anaheim, CA


    Erscheinungsdatum :

    01.09.1975


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch