Landing gear actuator systems and methods are disclosed. A landing gear actuator system may have an actuator body, an operating apparatus, a gas pressure adjustment apparatus, and a hydraulic fluid adjustment apparatus. The gas pressure adjustment apparatus may adjust at least one gas pressure in response to the operating apparatus. The hydraulic fluid adjustment apparatus may adjust at least one hydraulic fluid volume in response to the operating apparatus. The gas pressure and the hydraulic fluid volume may adjusted inversely. An isolation valve may be installed between the gas pressure adjustment apparatus and a strut gas chamber of a landing gear. In this manner, a landing gear strut may be shrunk without inducing high pressure in the strut, and stowed for flight, and a landing gear strut may be unshrunk and isolated by the valve to protect the actuator from high pressure and reaction forces during landing.


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    Titel :

    Shrinking System for Landing Gear


    Beteiligte:
    LUCE WILLIAM E (Autor:in)

    Erscheinungsdatum :

    2015-10-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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