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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    Title :

    Nitrogen powers Little Joe's open hydraulic system


    Additional title:

    Hydraulics Pneumatics


    Contributors:

    Published in:

    Publication date :

    1966


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




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