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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    Titel :

    Hydraulic apparatus for aircraft actuators


    Weitere Titelangaben:

    Hydraulikvorrichtung für Flugzeugbetätiger
    Appareil hydraulique pour actionneurs d'avion


    Beteiligte:
    FUKUI ATSUSHI (Autor:in)

    Erscheinungsdatum :

    28.11.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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