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 deicing and anti-icing system for an aircraft engine pod, including an air intake provided with a lip followed by an air intake tubular part, equipped with a first sound attenuating panel, including deicing means having at least one array of resistive heating elements embedded in an insulating material, the deicing means being in the form of a mat incorporating the resistive element in the thickness of the air intake lip.

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), characterised 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: 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: The invention relates to a panel for an acoustic treatment at the surface of an aircraft, that comprises from the outside to the inside an acoustically resistive porous layer, at least one cellular structure and a reflective or non-permissive layer, wherein the acoustically resistive porous layer includes, at the outer surface that may contact the aerodynamic flows of a sheet or foil, open areas (14) permissive to sound waves and solid area (6) not permissive to sound waves, characterised in that the sheet or foil of the acoustically resistive layer includes sets of microperforations (18), each set of microperforations defining an open area (14), the set of microperforations being separated by at least one series of spaced bands of solid areas (16).

Abstract: A process for the producing a coating for acoustic treatment relative to a leading edge such as an air intake of an aircraft nacelle, the coating including a reflective layer, an alveolar structure, and an acoustically resistive layer, includes: Digitizing the shape of the alveolar structure that it will have when it will be installed at the surface to be treated, Positioning in a virtual manner—so as to define their geometries—two series of bands so as to delimit a tube between, two adjacent bands of a first series, and two second adjacent bands of a second series, Cutting out each band according to their geometries defined above, Producing cut-outs in each band to allow the assembly of the bands, Assembling the bands so as to obtain an alveolar structure that has shapes that are suited to the surface to be treated.

Abstract: According to the invention, the air intake (2) is made of a piece (23) of fibre/resin composite material, reinforced on the side of the flange (24) by a reinforcing ring (26).

Abstract: A sound attenuation panel includes a resistive layer with a reinforced structural component, comprising at least a honeycomb structure (1) flanked, on one side, with a resistive layer (2) consisting of at least a porous layer (2b) and of at least a perforated structural layer (2a), and, on the other side, with a layer forming a total reflector (3). The structural layer (2a) is perforated with non-circular holes (4) having each its largest dimension and its smallest dimension along respectively two perpendicular axes. The panel is particularly applicable to pods for aeroplane jet engines.

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: Tooling for molding with keys for the production of air intakes without clips of substantially tubular shape, comprises a self-supporting mandrel with keys comprising at least three sectors in the form of panels, namely at least two articulated sectors (3) retractable toward the center of the mandrel and a key sector independent from the other sectors and insertable between these latter, thereby, by abutment, to define, by their external surfaces, a continuous surface corresponding to the internal surface of the air intake, elements to lock in abutted position the sectors, and a control device, disconnectable from the mandrel, of the relative displacement of the movable sectors to place them either in a molding position by abutment of the sectors, or in an unmolding position by retraction of the sectors toward the interior of the mandrel.

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: A connecting device for connecting first and second tubular pieces of an aircraft turbine engine may include a rigid ring with an at least approximately S-shaped cross section. The rigid ring is housed in a recess of an acoustic protection cellular core of the first tubular piece and includes: (1) an external branch, which bears against an external skin of the second tubular piece and is secured to the latter by a first fixing device; (2) a back, arranged facing an edge face of the cellular core; (3) a front arranged facing the first tubular piece, after the first and second tubular pieces have been connected; (4) a transverse branch connecting the back to the front; and (5) an internal branch connected to an internal skin of the second tubular piece and secured to the latter.

Abstract: The invention concerns a sound attenuation panel comprising a resistive layer with a reinforced structural component, comprising at least a honeycomb structure (1) flanked, on one side, with a resistive layer (2) consisting of at least a porous layer (2b) and of at least a perforated structural layer (2a), and, on the other side, with a layer forming a total reflector (3). The invention is characterized in that said structural layer (2a) is perforated with non-circular holes (4) having each its largest dimension and its smallest dimension along respectively two perpendicular axes. The invention is particularly applicable to pods for aeroplane jet engines.

Abstract: Tooling for molding with keys for the production of air intakes without clips of substantially tubular shape, comprises a self-supporting mandrel with keys comprising at least three sectors in the form of panels, namely at least two articulated sectors (3) retractable toward the center of the mandrel and a key sector independent from the other sectors and insertable between these latter, thereby, by abutment, to define, by their external surfaces, a continuous surface corresponding to the internal surface of the air intake, elements to lock in abutted position the sectors, and a control device, disconnectable from the mandrel, of the relative displacement of the movable sectors to place them either in a molding position by abutment of the sectors, or in an unmolding position by retraction of the sectors toward the interior of the mandrel.

Abstract: Device for connecting two tubular pieces of an aircraft turbine engine.

Abstract: An acoustic panel with several degrees of freedom comprises a resistive layer (14), a compartmentalized structure (16) formed from at least two superposed compartmentalized layers (18) and a back reflector (17), starting from an outside face facing an incident acoustic wave. A porous separator (24) is placed between each pair of adjacent compartmentalized layers. On each of its faces, this separator is fitted with tubular guides (26) that penetrate into at least some of the cells (20) of the compartmentalized layers. This thus aligns the cells over the entire thickness of the compartmentalized structure (24), regardless of the shape of the panel.

Abstract: An acoustic panel with several degrees of freedom comprises a resistive layer (14), a compartmentalized structure (16) formed from at least two superposed compartmentalized layers (18) and a back reflector (17), starting from an outside face facing an incident acoustic wave. A porous separator (24) is placed between each pair of adjacent compartmentalized layers. On each of its faces, this separator is fitted with tubular guides (26) that penetrate into at least some of the cells (20) of the compartmentalized layers. This thus aligns the cells over the entire thickness of the compartmentalized structure (24), regardless of the shape of the panel.