Disclosed is a leading edge structure (1) for a flow control system of an aircraft (101), comprising a double-walled leading edge panel (3) that surrounds a plenum (7) in a curved manner, wherein the leading edge panel (3) has a first side portion (11) extending to a first attachment end (17), wherein the leading edge panel (3) has a second side portion (13) extending to a second attachment end (19), wherein the leading edge panel (3) comprises an inner wall element (21) facing the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97), wherein the outer wall element (23) comprises a plurality of micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25), and wherein the inner wall element (21) comprises openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The object, to provide a leading edge structure that allows for a minimized thickness of the outer wall element, is achieved in that at the first attachment end (17) and/or at the second attachment end (19) the outer wall element (23) is attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).


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    Title :

    LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT


    Additional title:

    VORDERKANTENSTRUKTUR FÜR EIN STRÖMUNGSLEITSYSTEM EINES FLUGZEUGS
    STRUCTURE DE BORD D'ATTAQUE POUR SYSTÈME DE COMMANDE D'ÉCOULEMENT D'UN AÉRONEF


    Contributors:

    Publication date :

    2023-11-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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