Abstract: The invention relates to a leading edge mobile flap (16) for a main wing of an aircraft, this flap including an aerodynamic skin (18) that has a bird impact-sensitive frontal area (24), and a rear skin (28) integral with the aerodynamic skin (18), the flap also comprising a plurality of ribs (34) spaced out along a leading edge longitudinal direction (X?). According to the invention, the flap additionally includes, between two directly consecutive ribs, a single rigid bird trajectory-deflecting wall (42) anchored to the skins (18, 28). Furthermore, in a cross-section taken along any plane orthogonal to the direction (X?), the wall (42) forms with a geometric chord (26) of the flap an angle (?1) with a value of less than 45°.

Abstract: The invention relates to a leading edge mobile flap (16) for a main wing of an aircraft, this flap including an aerodynamic skin (18) that has a bird impact-sensitive frontal area (24), and a rear skin (28) integral with the aerodynamic skin (18), the flap also comprising a plurality of ribs (34) spaced out along a leading edge longitudinal direction (X?). According to the invention, the flap additionally includes, between two directly consecutive ribs, a single rigid bird trajectory-deflecting wall (42) anchored to the skins (18, 28). Furthermore, in a cross-section taken along any plane orthogonal to the direction (X?), the wall (42) forms with a geometric chord (26) of the flap an angle (?1) with a value of less than 45°.

Abstract: A structure (10) in the shape of an aerodynamic panel in which adjacent cells (20a, 20b) are formed by placing a stack of three metal plates in a mold. After diffusion welding of the plates at the required locations, a first variable pressure is applied in a first series of cells (20a) formed between the outer plate and the intermediate plate and a second independent pressure approximately constant and lower than the first is applied in the other cells (20b) and on the inner face of the stack. Thus, this partially forms the cells and shapes the structure in contact with a complementary surface of the mold. The final conformation of the cells and the structure is obtained by applying a second pressure cycle in the cells and on the inner face of the stack.

Abstract: A structure (10) in the shape of an aerodynamic panel in which adjacent cells (20a, 20b) are formed by placing a stack of three metal plates in a mould. After diffusion welding of the plates at the required locations, a first variable pressure is applied in a first series of cells (20a) formed between the outer plate and the intermediate plate and a second independent pressure approximately constant and lower than the first is applied in the other cells (20b) and on the inner face of the stack. Thus, this partially forms the cells and shapes the structure in contact with a complementary surface of the mould. The final conformation of the cells and the structure is obtained by applying a second pressure cycle in the cells and on the inner face of the stack.