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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Payload separation and thrust termination in solid-propellant rocket motor


    Weitere Titelangaben:

    Aerospace Eng


    Beteiligte:
    Sehgal, R. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1962


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :