Solid propellant launch vehicle, Little Joe II, applied for flight testing launch escape system of Apollo space vehicle; components were combined into nonrecirculating hydraulic systems mounted on four missile fins; vehicle attitude is controlled with aerodynamic control surface on each of four fins; each control surface is powered by its own separate hydraulic system located within and on each fin; each complete fin system may be operated separately or four fins may be operated simultaneously by autopilot system; each complete fin is replaceable if hydraulic system malfunctions during vehicle checkout.


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    Titel :

    Nitrogen powers Little Joe's open hydraulic system


    Weitere Titelangaben:

    Hydraulics Pneumatics


    Beteiligte:
    Oberst, R.S. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    5 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




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