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.


    Access

    Download


    Export, share and cite



    Title :

    LEADING EDGE SLAT WITH OPTIMIZED STRUCTURE


    Contributors:

    Publication date :

    2020-07-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



    Leading edge slat with optimized structure

    HERMEL PASCAL / GAUTRAND LUC / BAUVIR FRANÇOIS et al. | European Patent Office | 2022

    Free access

    Leading edge slat

    COMMIS BEN / LYONS NEIL / KAY EDMUND | European Patent Office | 2022

    Free access

    Leading edge slat

    COMMIS BEN / LYONS NEIL / KAY EDMUND | European Patent Office | 2024

    Free access

    LEADING EDGE SLAT

    COMMIS BEN / LYONS NEIL / KAY EDMUND | European Patent Office | 2021

    Free access

    LEADING EDGE SLAT

    COMMIS BEN / LYONS NEIL / KAY EDMUND | European Patent Office | 2025

    Free access