METHOD FOR THE PRODUCTION OF A COMPOSITE TRAILING EDGE PANEL FOR AN AIRCRAFT ELEMENT

摘要

The invention relates to a method for producing a structural composite trailing edge panel (1) for an aircraft element having: an upper surface (3), a lower surface (5), and a trailing edge (7) connecting said upper (3) and lower (5) surfaces, the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9), at least one longitudinal spar (10) being positioned in such a way that the directrix (&Dgr;10) of each longitudinal spar (10) and the directrix (&Dgr;9) of the transverse stiffeners (9) are not collinear and the structuring panel (1) being made up of a one-piece component forming the upper surface (3), the lower surface (5), the trailing edge (7), the transverse stiffeners (9) and the spar or spars (10).