公开(公告)号：US11260956B2

公开(公告)日：2022-03-01

申请号：US16727189

申请日：2019-12-26

申请人： DAHER AEROSPACE

发明人： Pascal Hermel ,  Luc Gautrand ,  François Bauvir ,  Arnaud Cazelles ,  David Clech

IPC分类号： B64C3/26 ,  B64C3/18 ,  B29L31/30 ,  B64C1/12 ,  B64C1/00

摘要： 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.