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 method for assembling sheets by riveting, comprising a step for piercing a hole through the sheets, followed by a step for placing a rivet in the pierced hole, the step for piercing a hole being executed by supplying an advance speed instruction of a piercing tool as well as a rotation speed instruction of this tool. According to the invention, a previous step for determining information on the local stiffness of the sheets (Info_stiffness) is also carried out at the level of the hole to be pierced, the advance speed instruction and rotation speed instruction of the tool being a function of this information on the local stiffness of the sheets. Application most suited to the field of aircraft construction.

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 panel, such as is intended for an aircraft wing panel, has continuous ribs extending on one surface. The panel is formed, or given a dihedral bend, by shot peening the ribs at a V-shaped section to expand the V-shaped sections and thus deform the panel. A strong formed panel is thus provided with continuous ribs. Further shot peening steps can be carried out on the panel for further shaping.

Abstract: Thin walled compartmented tubular structure and its manufacturing process. The elbow or T-shaped structure, includes an external wall (14)and continuous internal walls (22) made in one piece. This therefore materializes, between the inlet (10) and each outlet (12) of the structure, at least one continuous passage to direct a fluid circulating inside it. The structure according to the invention is manufactured by diffusion welding and superplastic forming, from titanium alloy sheets. One application is for aircraft de-icing circuits.

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: Composite joint for fitting at least one external member to a sandwich panel and panel integrating at least one such joint. To permit the transmission of static and/or dynamic stresses between at least one external member and a sandwich panel, into said panel is integrated at least one composite joint (10). Said joint comprises a plurality of juxtaposed, elementary, tubular cells (12), oriented in the panel thickness direction, as well as at least one stress introduction cell (12a), in which is fitted a rigid part (14) for fixing the external member. The tubular cells (12) comprise composite walls formed from braided fiber roves and resin.

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.

Abstract: Process for assembly of a flexible panel on an open structure, and installation to make use of this process. According to the invention, a flexible panel (12) is attached to an open structure (10) by pre-assembling these two parts by cold gluing before they are fixed using attachment devices such as rivets. Cold gluing is done using a gluing cap (48) on the inside of which linear and individual inflatable joints (54, 56) are fitted to press the panel (12) into contact with the framework (10) in unperforated parts of the framework. The time necessary for assembly is thus very much reduced, while the quality of part positioning is unaffected.

Abstract: Thin walled compartmented tubular structure and its manufacturing process.