An aircraft wing (101) comprising a flap system (103) that is mounted at a leading or trailing edge (105, 107) of the wing (101) and comprises at least two movable flap devices (109, 111) spaced apart in a spanwise direction Y from each other, wherein each movable flap device (109, 111) is supported by at least one support station (203, 205) and is driven about a hinge axis (119) by at least one drive system (115), wherein the flap system (103) further comprises a synchronising torque element (113) connected to the movable flap devices (109, 111), wherein the synchronising torque element (113) is configured to transmit a torque between the movable flap devices (109, 111) in order to actuate a rotational movement of the movable flap devices (109, 111), and wherein the synchronising torque element (113) is positioned between the movable flap devices (109, 111) and around an adjacent system or structural component (116) that is also positioned between the movable flap devices (109, 111).


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    Titel :

    AIRCRAFT FLAP SYSTEM


    Weitere Titelangaben:

    FLUGZEUGKLAPPENSYSTEM
    SYSTÈME DE VOLETS D'AÉRONEF


    Beteiligte:

    Erscheinungsdatum :

    03.07.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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