A pump unit installed inside a wing (102) includes a backup hydraulic pump (20) that can supply pressure oil to an actuator (104) when a loss or reduction occurs in the function of an aircraft central hydraulic power source (105) and an electric motor that drives the pump. A wing structure (102) portion forming the surface structure of the wing is provided with an inlet port and an exhaust port that are formed therethrough. The inlet port is provided so as to be opened and closed by an inlet port opening/closing portion, and the exhaust port is provided so as to be opened and closed by an exhaust port opening/closing portion.


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    Title :

    Hydraulic apparatus for aircraft actuators


    Additional title:

    Hydraulikvorrichtung für Flugzeugbetätiger
    Appareil hydraulique pour actionneurs d'avion


    Contributors:

    Publication date :

    2018-11-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Hydraulic apparatus for aircraft actuators

    NAKAGAWA SHINGO / FUKUI ATSUSHI | European Patent Office | 2018

    Free access

    Hydraulic system for aircraft actuators

    FUKUI ATSUSHI / SHIRAI YASUYUKI | European Patent Office | 2015

    Free access