A leading edge slat of a wing element of an aircraft. The aircraft defining a mark including a main fuselage axis x and a spanwise axis y. The wing procuring a lift along an axis z. The wing element having a skin forming the leading edge slat, a spar linked to the skin and a stiffening structure linked on the leading edge side to the spar and to the skin. The stiffening structure being formed from a formed sheet metal having a plurality of bosses distributed according to the length of the leading edge. The bosses extending between the spar and the inner face of the skin.


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    Titel :

    LEADING EDGE SLAT WITH OPTIMIZED STRUCTURE


    Beteiligte:
    HERMEL PASCAL (Autor:in) / GAUTRAND LUC (Autor:in) / BAUVIR FRANÇOIS (Autor:in) / CAZELLES ARNAUD (Autor:in) / CLECH DAVID (Autor:in)

    Erscheinungsdatum :

    02.07.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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