Command method for thrust reduction and/or thrust termination of rocket motor project Shavetail was demonstrated in flight by Jet Propulsion Laboratory; investigation of time-acceleration relationship of payload after motor separation, as function of effective orifice opening of thrust termination and pressure variation with time; analytical model and equations to predict parameters; capability for velocity control of payload is outlined; results are compared with flight-test data on axial acceleration of payload during thrust termination of Shavetail system.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Payload separation and thrust termination in solid-propellant rocket motor


    Additional title:

    Aerospace Eng


    Contributors:
    Sehgal, R. (author)

    Published in:

    Publication date :

    1962


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :