A landing gear retraction/extension device includes a hydraulic actuator (2), a hydraulic circuit, a hydraulic pump (5), an electric motor (6), and a driver (61). Part of the hydraulic circuit is provided such that heat is exchangeable between operation oil and each of the electric motor (6) and the driver (61). The driver (61) supplies power to the electric motor before landing of an aircraft such that an operation oil temperature is higher than a predetermined temperature upon the landing of the aircraft.


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    Title :

    Landing gear retraction/extension device of aircraft


    Additional title:

    Fahrwerkauszugs-/einzugsvorrichtung eines Flugzeugs
    Dispositif de rétraction/extension de train d'atterrissage d'un aéronef


    Contributors:
    ONOMICHI YASUTO (author) / KONDO TAKU (author) / HAGIHARA SHOGO (author) / TAKAKI RYO (author) / ONISHI TAKAAKI (author)

    Publication date :

    2016-01-20


    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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