An aircraft wing including a flap system mounted at a leading or trailing edge of the wing and includes at least two movable flap devices spaced apart in a spanwise direction Y from each other, each movable flap device supported by at least one support station and driven about a hinge axis by at least one drive system. The flap system includes a synchronizing torque element connected to the movable flap devices, wherein the synchronizing torque element is configured to transmit a torque between the movable flap devices to actuate a rotational movement of the movable flap devices, and wherein the synchronizing torque element is positioned between the movable flap devices and around an adjacent system or structural component that is also positioned between the movable flap devices.


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    Titel :

    AIRCRAFT FLAP SYSTEM


    Beteiligte:

    Erscheinungsdatum :

    2024-07-04


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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