A landing gear lifting/lowering EHA system (10) includes: a hydraulic actuator (2) configured to lift and lower the leg of an aircraft; at least one electrically operated hydraulic pump (31, 32); a hydraulic path (101); a pressure sensor (38, 39) attached to the hydraulic actuator or the hydraulic path and configured to output a measurement signal corresponding to hydraulic pressure; and a controller (9) configured to output a control signal to the electrically operated hydraulic pump, wherein, when a state in which the hydraulic pressure exceeds a set pressure continues for a set time, the control unit stops the electrically operated hydraulic pump in operation and resumes the operation of the electrically operated hydraulic pump after the hydraulic pressure drops to or below a second set pressure after the electrically operated hydraulic pump is stopped.


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    Title :

    LANDING GEAR LIFTING/LOWERING EHA SYSTEM


    Additional title:

    HUB- UND SENKVORRICHTUNG FÜR EIN FAHRWERK
    SYSTÈME D'ACTIONNEUR ÉLECTRO-HYDRAULIQUE DE LEVAGE/ABAISSEMENT DE TRAIN D'ATTERRISSAGE


    Contributors:

    Publication date :

    2023-05-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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