METHOD FOR MANUFACTURING A COMPOSITE PANEL WITH A CHAMFER AND THE CORRESPONDING COMPOSITE PANEL

Abstract

The invention relates to a method for manufacturing (100) a composite panel (13) for an aircraft turbomachine (1), the method comprising the following steps: - production (110) of a first skin (14) in a composite material comprising a fibrous reinforcement densified by a first polymer matrix, - production (120) of at least one reinforcing edge (20) from the first skin (14) by additive manufacturing, the reinforcing edge (20) being made of a thermoplastic material, - application (130) of a core (16) with a honeycomb structure onto the first skin (14) and adjacently to the reinforcing edge (20), - production (140) of a second skin (15) in a composite material comprising a fibrous reinforcement densified by a second polymer matrix, onto the honeycomb-structured core (16) and at least a portion of the reinforcing edge (20). Figure for the abstract: Fig. 3