A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).


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    Titel :

    LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT


    Beteiligte:
    BERTOLINI IVANO (Autor:in) / GIAQUINTO STEFANO (Autor:in) / WELZ SEBASTIAN (Autor:in) / DÜREN NINA (Autor:in) / YAP JEFF WEE HONG (Autor:in) / HÖFT MICHAEL (Autor:in) / JORDAN NICOLE (Autor:in)

    Erscheinungsdatum :

    28.07.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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