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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    Titel :

    Hydraulic apparatus for aircraft actuators


    Weitere Titelangaben:

    Hydraulikvorrichtung für Flugzeugbetätiger
    Appareil hydraulique pour actionneurs d'avion


    Beteiligte:
    NAKAGAWA SHINGO (Autor:in) / FUKUI ATSUSHI (Autor:in)

    Erscheinungsdatum :

    2018-10-10


    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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