| 摘要 |
Method of fabricating a fibrous reinforcement (1) for a composite-material component which includes a panel provided with a rib. According to the invention, transverse fibres (4A) are inserted, through the face of the first fibrous element (2) opposite the second fibrous element (3) and by the stitching, without knotting, of a continuous filament (4) with the aid of a needle (33,40), over the entire extent of the said first fibrous element (2) in such a way that the said transverse fibres (4A), which face the bearing flange (3A) of the said second fibrous element (3), form stitches (4B) fastening together the said first and second fibrous elements and in such a way that some (4A1) of the said transverse fibres (4A) are vertically in line with the stiffening flange (3B) of the said second fibrous element (3). Fabrication of composite components of the aircraft-panelling type. <IMAGE> |
