Hydraulic actuator 202 (e.g. for aircraft landing gear) having an extension chamber 206 and a retraction chamber 208, and a bypass line 222 connecting and short circuiting the two chambers, the bypass line having flow restrictor 224 and a bypass valve 226 (e.g. in series). The valve may be manually actuated (e.g. directly, or via a tool by a human). The valve may further be electromechanically driven. Flow restrictor orifice may have 4 to 14 mm2 cross-sectional area. A valve status sensor may sense valve position or hydraulic fluid parameter in the bypass line. The bypass line may be external to the hydraulic ram connecting to the hydraulic lines 216, 218, within the wall of the hydraulic ram housing, or within the moveable piston 204.


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    Title :

    Hydraulic actuator


    Contributors:
    SEAN KERR (author)

    Publication date :

    2025-06-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein / B64C AEROPLANES , Flugzeuge



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