A pump unit (12) installed inside a wing (100), and a panel body (11) constituting part of a wing structure portion forming a surface structure of the wing (100) are provided. The pump unit (12) includes a backup hydraulic pump (13) that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor (14) that drives this pump. Except for at least the panel body, the wing structure portion is formed from fiber reinforced plastics. The panel body (11) is formed of a metallic material.


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    Title :

    Hydraulic apparatus for aircraft actuators


    Additional title:

    Hydraulikvorrichtung für Flugzeugbetätiger
    Appareil hydraulique pour actionneurs d'avion


    Contributors:

    Publication date :

    2018-10-10


    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