Abstract: A system for dual management of anti-icing and boundary layer suction for an aerofoil of an aircraft, including: at least one anti-icing channel and at least one suction channel; a device monitoring boundary layer suction and a device monitoring anti-icing; a first duct collecting the suction air communicating with the suction channel and a second duct supplying anti-icing air connected to the device and communicating with the anti-icing channel; a three-way valve to which the first duct, a suction duct, and a duct for discharging the anti-icing air are connected; and a duct collecting anti-icing air connected to the anti-icing channel, and to the first duct.

Abstract: For dual management of anti-icing and boundary-layer suction, a system for an aerofoil of an aircraft, including: a channel having a double function of anti-icing and boundary-layer suction; a double-function main pipe to which a device for monitoring the boundary-layer suction and a device for monitoring anti-icing are connected; an anti-icing air-intake pipe connecting the main pipe and the channel; a non-return valve enabling anti-icing air to go from the main pipe to the pipe; at least one suction-air collection pipe connecting the channel and the main pipe; and a non-return valve enabling suction air to pass from the pipe toward the main pipe.

Abstract: A system for dual management of anti-icing and boundary layer suction for an aerofoil of an aircraft, including: at least one anti-icing channel and at least one suction channel; a device monitoring boundary layer suction and a device monitoring anti-icing; a first duct collecting the suction air communicating with the suction channel and a second duct supplying anti-icing air connected to the device and communicating with the anti-icing channel; a three-way valve to which the first duct, a suction duct, and a duct for discharging the anti-icing air are connected; and a duct collecting anti-icing air connected to the anti-icing channel, and to the first duct.

Abstract: For dual management of anti-icing and boundary-layer suction, a system for an aerofoil of an aircraft, including: a channel having a double function of anti-icing and boundary-layer suction; a double-function main pipe to which a device for monitoring the boundary-layer suction and a device for monitoring anti-icing are connected; an anti-icing air-intake pipe connecting the main pipe and the channel; a non-return valve enabling anti-icing air to go from the main pipe to the pipe; at least one suction-air collection pipe connecting the channel and the main pipe; and a non-return valve enabling suction air to pass from the pipe toward the main pipe.

Abstract: The invention relates to a process for manufacturing a sandwich panel comprising a step to bake a stacked structure (16) provided with: a honeycomb body (2); a film (12) pre-impregnated with a first resin with a polymerization temperature T1; and a first stack (18) of fiber layers pre-impregnated with a second resin with a polymerization temperature T2 greater than T1, the film being arranged between the first stack and the body. The baking step comprises a first phase designed to use the film (12), to create a rigid barrier providing a seal from the second resin by polymerization of said first resin, followed by a second phase designed to produce the skin starting from the stack (18), by polymerization of the second resin.

Abstract: A method for producing a skin of a leading edge for an aircraft wing element, including an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge. The method includes curing a stack in a mold between two molding surfaces facing each other. The stack includes the resistive heating elements assembly, two adhesive films arranged respectively on either side of the assembly so that the heating elements adhere to each of these two adhesive films, two layers of electrically insulating pre-impregnated fibers adhering respectively to the two adhesive films on the sides opposite those receiving the heating elements, and a plurality of layers of pre-impregnated carbon fibers.

Abstract: A method for producing a skin of a leading edge for an aircraft wing element, including an assembly of resistive heating elements designed to form an integral part of a system for de-icing and/or anti-icing of the leading edge. The method includes curing a stack in a mould between two moulding surfaces facing each other. The stack includes the resistive heating elements assembly, two adhesive films arranged respectively on either side of the assembly so that the heating elements adhere to each of these two adhesive films, two layers of electrically insulating pre-impregnated fibres adhering respectively to the two adhesive films on the sides opposite those receiving the heating elements, and a plurality of layers of pre-impregnated carbon fibres.

Abstract: The invention relates to a process for manufacturing a sandwich panel comprising a step to bake a stacked structure (16) provided with: a honeycomb body (2); a film (12) pre-impregnated with a first resin with a polymerisation temperature T1; and a first stack (18) of fibre layers pre-impregnated with a second resin with a polymerisation temperature T2 greater than T1, the film being arranged between the first stack and the body. The baking step comprises a first phase designed to use the film (12), to create a rigid barrier providing a seal from the second resin by polymerisation of said first resin, followed by a second phase designed to produce the skin starting from the stack (18), by polymerisation of the second resin.

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: Thin walled compartmented tubular structure and its manufacturing process.