Abstract: A method is provided for destroying a blind fastener joining at least two parts. The blind fastener includes, but is not limited to a body situated in the holes provided in the joined parts, with a head at each end thereof, and portions of which protrude above the level of the holes. The method also includes, but is not limited to withdrawing the accessible head of the fastener, and creating a hole that passes through the fastener. An insertion device is configured to restrain the remainder of the fastener in the hole, which has an elongated body having a diameter smaller than or equal to that of the hole and an expandable head at one end thereof The insertion device for restraining the remainder of the fastener being immobilised or capable of only limited movement relative to the joined parts, and expelling the remainder of the fastener from the holes.

Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.

Abstract: An aircraft nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel.

Abstract: A noise reduction assembly located at a junction plane between an air intake structure and a fan casing of an aircraft turbojet has improved acoustic properties since the alternation of acoustic and non-acoustic zones is displaced or eliminated. In particular, the inner wall of the air intake structure includes a projecting part that extends towards the aft direction beyond the junction plane, in other words the flange of the fan casing. The projecting part may be sufficiently long so that its inner skin is continuous as far as the limit between the acoustic zone and the non-acoustic zone of the nacelle.

Abstract: An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.

Abstract: An acoustic treatment panel includes, from the inside to the outside, a reflective layer (50), at least one alveolar structure (52), and at least one acoustically resistive structure (54) that forms an aerodynamic surface, whereby the panel is connected at one edge to at least one second panel (46), characterized in that it includes, at the edge overlapping with the at least one second panel, a reinforcement (60) that is inserted between the reflective layer (50) and the acoustically resistive structure (54) forming the aerodynamic surface, whereby the reinforcement (60) ensures the uptake of forces between the layer (50) and the structure (54).

Abstract: The object of the invention is an aircraft nacelle that comprises at least one part, called a door (14), that moves relative to a stationary part (20) and a connecting device that makes it possible to limit the offset between said door and said stationary part in a direction that corresponds to the primary direction of the flow of air outside of the nacelle during flight, whereby said device comprises, on the one hand, an indexer (40) that is connected to the door (14) that comprises an attachment surface (63) and at least one attachment element (66), and, on the other hand, at least one stop (58) that is connected to the stationary part (20) against which said indexer (40) can rest in such a way as to limit its movement in said direction, characterized in that said at least one attachment element (66), oriented in the radial direction, is arranged upstream from the stop (58) in said direction, said at least one stop (58) comprising a surface relative to the door arranged essentially at the attachment surface

Abstract: An acoustic treatment structure related to a leading edge onto which an aerodynamic stream flows, in particular at an air intake of an aircraft nacelle, includes—from the outside to the inside—at least one acoustically resistive substructure (30), at least one alveolar substructure including strips (32) of cells, arranged in a direction that is essentially perpendicular to the direction of flow of the aerodynamic stream, and at least one reflective layer (34). Each strip (32) includes a first part that insulates the strips from one another, called a support, with a U-shaped cross-section in the longitudinal direction, whose open surface that is opposite to the bottom of the U shape is flattened against the acoustically resistive substructure (30), and at least a second part, called partitioning, making it possible to partition the space that is delimited by the support and the acoustically resistive substructure (30) into cells.

Abstract: A wall panel of composite material including at least two carbon fiber layers oriented parallel to the plane of the panel and embedded in a resin matrix. At least one reinforcement mesh is inserted between the two fiber layers. The mesh has at least a first series of linear elements with a section greater than or equal to 0.07 mm2 The reinforcement mesh is embedded in the resin matrix, and the two layers arranged on both sides of the mesh are linked in all zones situated between the linear elements of the mesh.

Abstract: An aircraft nacelle includes a first subassembly consisting of a pipe (112) channeling an airflow in the direction of an engine having a covering or panel (118) for acoustic treatment, including, from the inside to the outside, a reflecting layer (120), at least one cellular structure (122), and at least one acoustically resistive structure (124) forming the aerodynamic surface of the pipe (112), as well as a second subassembly consisting of a lip (116) and a front frame (126), characterized in that it includes at least one connection element (134) which is separate from the two subassemblies and connected to a portion of the pipe (112) and to a portion of the lip forming an extension of the portion of the pipe at different points so as to be capable of enabling a relative movement between the two subassemblies.

Abstract: The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer (28), at least one cellular structure (30) and a reflective layer (32), characterized in that it comprises ducts (34) provided between said cellular structure (30) and the acoustically resistive structure (28), the ducts being each defined by a wall (36) separate from the walls of the cellular structure (30) and one end of the ducts being connected to a hot air supply.

Abstract: An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.

Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.

Abstract: An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.

Abstract: The object of the invention is an aircraft nacelle that comprises at least one part, called a door (14), that moves relative to a stationary part (20) and a connecting device that makes it possible to limit the offset between said door and said stationary part in a direction that corresponds to the primary direction of the flow of air outside of the nacelle during flight, whereby said device comprises, on the one hand, an indexer (40) that is connected to the door (14) that comprises an attachment surface (63) and at least one attachment element (66), and, on the other hand, at least one stop (58) that is connected to the stationary part (20) against which said indexer (40) can rest in such a way as to limit its movement in said direction, characterized in that said at least one attachment element (66), oriented in the radial direction, is arranged upstream from the stop (58) in said direction, said at least one stop (58) comprising a surface relative to the door arranged essentially at the attachment surface

Abstract: An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.

Abstract: A panel for acoustic treatment connected to a surface of an aircraft, includes—from the outside to the inside—an acoustically resistive porous layer, at least one alveolar structure, and a reflective or impermeable layer, whereby the acoustically resistive porous layer includes—at the outside surface that can be in contact with the aerodynamic flows—one sheet or piece of sheet metal including open zones (14) that allow sound waves to pass and filled zones (16) that do not allow sound waves to pass, characterized in that the sheet or piece of sheet metal of the acoustically resistive layer includes sets of microperforations (18), whereby each set of microperforations forms an open zone (14), the sets of microperforations being separated from one another by at least one series of bands separated by filled zones (16).

Abstract: An aircraft nacelle includes an air intake for channeling air flow in the direction of a power plant. The air intake includes an inside pipe that forms an aerodynamic surface in contact with the air flow and is extended toward the rear by an aerodynamic surface of a pipe of the power plant. The nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel.

Abstract: A process for the production of an acoustically resistive structure that can be inserted in an alveolar structure so as to obtain a coating for the acoustic treatment, whereby the acoustically resistive structure includes at least one porous layer (34) and at least one reinforcement structure (36) assembled by gluing, the process including: applying an amorphous-type adhesive on the at least one reinforcement structure (36), perforating or micro-perforating the reinforcement structure (36) after the application of the amorphous-type adhesive, and applying the at least one porous layer against the face of the reinforcement structure (36) that is coated with amorphous-type adhesive.

Abstract: An acoustic treatment panel includes, from the inside to the outside, a reflective layer (50), at least one alveolar structure (52), and at least one acoustically resistive structure (54) that forms an aerodynamic surface, whereby the panel is connected at one edge to at least one second panel (46), characterized in that it includes, at the edge overlapping with the at least one second panel, a reinforcement (60) that is inserted between the reflective layer (50) and the acoustically resistive structure (54) forming the aerodynamic surface, whereby the reinforcement (60) ensures the uptake of forces between the layer (50) and the structure (54).