A hydraulic actuator system 1 is provided for driving a movable portion attached to a wing 5 of an airplane. A plurality of first system hydraulic actuators 2 and a plurality of second system hydraulic actuators 3 are included and are connected to the movable portion. The first system hydraulic actuators 2 are attached to the wing 5 and connected to a first hydraulic pressure source, whereas the second system hydraulic actuators 3 are attached to the wing to be in parallel to the first system hydraulic actuators 2 and are connected to a second hydraulic pressure source. The first system hydraulic actuators 2 and the second system hydraulic actuators 3 are alternately provided at a predetermined part of the wing 5.


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    Titel :

    Hydraulic actuator system for aircraft


    Weitere Titelangaben:

    Hydraulisches Aktuatorsystem für Flugzeuge
    Système d'actionneur hydraulique pour aéronefs


    Beteiligte:
    SUZUKI KAZUYUKI (Autor:in) / ITOH KOJI (Autor:in)

    Erscheinungsdatum :

    23.08.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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