An aircraft hydraulic actuation system comprises a supply line carrying hydraulic fluid pressurised by a pump, a return line returning hydraulic fluid to a reservoir, and a hydraulic actuator 128. In a first operation mode (figure 8a) a first chamber 130 (230, figure 9) of the actuator is supplied with pressurised hydraulic fluid from the supply line and piston 134 (234) is moved in a first direction, moving a load (e.g. door or landing gear). In a second operation mode (figure 8b) the first chamber is taken out of fluid communication with the supply line, a second chamber 132 (232, figure 9) is in fluid communication with the return line and the piston is moved under the load (e.g. landing gear extends under gravity). Preferably, a hydraulic fluid flow path 144 (244) having a flow restrictor 146 (246) (e.g. orifice, through hole 244 or valve) is provided between the chambers.


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    Titel :

    Hydraulic actuation system for an aircraft


    Beteiligte:
    PAUL GORDON L'ALLIER (Autor:in) / ANDY MOUNTY (Autor:in) / SEAN KERR (Autor:in)

    Erscheinungsdatum :

    03.03.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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