A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) surrounding a plenum (7). The leading edge panel (3) has 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 the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97). The outer wall element (23) includes micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25). The inner wall element (21) includes openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The outer wall element (23) extends from the first attachment end (17) to the second attachment end (19).


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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) / JORDAN NICOLE (Autor:in) / NIELSEN FRANK (Autor:in)

    Erscheinungsdatum :

    23.04.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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