The fuel pressurization system is for use in an aerial missile for maintaining its center of gravity between prescribed limits. Two fuel tanks are arranged forward and aft in a missile, both tanks having expandable bladders therein which, when expanded by a pressurized gas, force fuel from the tanks. Admission of gas to the aft tank is controlled by an actuator operated normally closed check valve which acts to prohibit fuel withdrawal from the tank until the forward tank is empty and the pressure in the outlet fuel line begins to fall. Consequently, in addition to maintaining a nearly constant center of gravity within the fuel tanks, the system also sustains the fuel pressure level above that value required for rocket engine combustion.


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    Titel :

    FUEL Pressurization System


    Beteiligte:
    W. W. Hagner (Autor:in)

    Erscheinungsdatum :

    1965


    Format / Umfang :

    1 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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