| 摘要 |
A method for producing a skin of a leading edge for an aircraft wing element, including an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge. The method includes curing a stack in a mould between two moulding surfaces facing each other. The stack includes the resistive heating elements assembly, two adhesive films arranged respectively on either side of the assembly so that the heating elements adhere to each of these two adhesive films, two layers of electrically insulating pre-impregnated fibres adhering respectively to the two adhesive films on the sides opposite those receiving the heating elements, and a plurality of layers of pre-impregnated carbon fibres. |
