US 2012/0267479 A1 · METHOD FOR THE PRODUCTION OF A COMPOSITE TRAILING EDGE PANEL FOR AN AIRCRAFT ELEMENT

Abstract

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 (Δ10) of each longitudinal spar (10) and the directrix (Δ9) 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).

Claims10

Dependent claims

A method for manufacturing a composite trailing edge panel for an aircraft element, comprising:

a first step in which first cores and at least one second core are positioned, each surrounded at least partially by a draping skin on a base skin, in two non-collinear directions, such that said base skin can be folded on itself;
a second step in which the base skin is folded on the first and second draped cores;
a third step in which the panel thus obtained is polymerized so as to integrate the plies of the draping into the base skin to form the transverse stiffeners and a longitudinal spar(s);
and
a fourth step in which the first cores and the second core(s) are removed so as to obtain the structural panel.

2 more elements

Dependencies are inferred from the claim text.

Method for the production of a composite trailing edge panel for an aircraft element

Life of this patent

Method for the production of a composite trailing edge panel for an aircraft element

Life of this patent

Abstract

Claims10