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.
BEC DE BORD D'ATTAQUE À STRUCTURE OPTIMISÉE
LEADING EDGE SLAT WITH OPTIMISED STRUCTURE
VORFLÜGEL MIT OPTIMIERTER STRUKTUR
2021-05-05
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2019
|European Patent Office | 2020
|European Patent Office | 2019
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