Theory is developed for internal aerodynamics of nozzle, to be employed as thrust vector control device of solid propellant rockets; theory is based on three-dimensional, small-perturbation treatment of originally undistributed supersonic source flow; nozzle scaling, pivot point location for minimum actuation power, splitline geometry effects, thrust-vector-deflection amplification and suppression, and implications of designing for low actuation torques are considered; comparison with experiment.


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    Title :

    Theory of aerodynamics of supersonic splitline gimbaled nozzle


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1967


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :





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