Patent ID: 8491829

Claim:
A process for the production of a structural part of an aircraft, said part being made of composite material that comprises a thermosetting resin and that has a section profile that can be stamped, said process comprising: producing a flat blank by draping layers of supports that are preimpregnated with thermosetting resin, curing the thermosetting resin to partially cross-link the resin in the flat blank, and performing a forming operation comprising: (i) stamping the partially cross-linked flat blank between a matrix and a punch, the matrix and punch being heated to a temperature of between 130° C. to 180° C., each of said matrix and punch comprising an impression that is adapted to a shape of a surface that is in contact with the part that is to be produced, and an air gap between the matrix and punch, the air gap having a size that is based on the part, and (ii) further cross-linking the partially cross-linked thermosetting resin in the stamped part under the temperature of between 130° C. to 180° C., wherein the matrix and punch are heated during and after the forming operation at a temperature of between 130° C. to 180° C., and for a period of time and at a temperature to modulate the cross-linking of the thermosetting resin so that the part is geometrically stable upon completion of the forming operation.