Abstract: A thrust reverser for an aircraft propulsion unit. The thrust reverser includes three gates that can be deployed downstream of an outlet section of the propulsion unit. The device increases the possibilities for installation of the reverser, in particular when a tail assembly extends in line with the propulsion unit.

Abstract: Aircraft having at least one propulsion unit supplied with hydrogen by at least one hydrogen tank, and having at least one thrust reversal system including at least one actuator. The aircraft can include at least one means for storing or transporting the residual hydrogen of the propulsion unit, a fuel cell disposed in the hydrogen power source and supplied with hydrogen by the at least one means for storing the residual hydrogen, and a hydrogen thrust reverser actuation system. The thrust reverser actuation system can include a hydrogen thrust reverser actuation controller and a hydrogen primary power unit with a fuel cell supplied with hydrogen and powering the at least one thrust reverser actuator.

Abstract: An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.

Abstract: A device for attaching a connecting rod small end for a thrust reversal cascade flap onto a fixed internal structure of a turbojet engine nacelle includes a fitting configured to be fixed to the internal structure and a connection interface forming a joint between the connecting rod small end and the fitting. The device further includes a removable fork configured to cooperate with the connection interface, wherein the fork and the connection interface are arranged inside the fitting.

Abstract: A nacelle for an aircraft propulsion unit includes an air intake cowl, and an intermediate section including fixed and removable hoods defining an access space between front ends of the hoods and an outer rear end of the air intake cowl. The intermediate section includes an annular row of mutually spaced connecting parts which rigidly connect the outer rear end of the air intake cowl to the front ends of the hoods so as to transmit longitudinal forces, and an intermediate cowl extending between the air intake cowl and the hoods, around the connecting parts, thereby closing the access space and creating aerodynamic continuity with the air intake cowl and the hoods. The intermediate cowl is formed from at least one strip which is held in place by tangential clamping of the circumferential ends of the strip.

Abstract: An acoustic panel for a turbine engine includes a first strip and a second strip each comprising an alternation of first ridges and second ridges connected by sidewalls. The first and second strips are joined to each other to form a plurality of cells, each delimited by a first ridge of the first strip and a first ridge of the second strip. A third strip is interposed between the first strip and the second strip and includes a first lateral wall bearing on the first strip The third strip further includes at least one tab that extends inside one of the cells and delimits all or part of a passage inside the associated cell.

Abstract: An aircraft propulsion assembly has a hinge for articulating a first and a second of its panels. The hinge includes a yoke rigidly connected to the first panel and a counter-yoke rigidly connected to the second panel, which is received between two lugs of the yoke. The yoke and the counter-yoke are passed through by a hinge pin that is movable between an extended position between the lugs of the yoke and a retracted position outside the yoke. The hinge further includes bayonet mounting means interposed between the pin and the yoke.

Abstract: Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.

Abstract: A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.

Abstract: A structure comprising a nacelle or a thrust reverser, the structure comprising a stationary part and a movable part, the structure comprising: a first guide provided on or in the stationary part of the structure or the movable part of the structure; a first electrical connector attached to the stationary part of the structure: a second electrical connector attached to the movable part of the structure; and a carriage movable along the first guide: wherein the carriage comprises a closed loop electrical cable mounted in or on a carriage body such that the closed loop cable can rotate, wherein the first electrical connector is electrically connected to the closed loop electrical cable and the closed loop electrical cable is electrically connected to the second electrical connector, thereby providing an electrical connection from the stationary part of the structure to the movable part of the structure.

Abstract: A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.

Abstract: The invention relates to an assembly (601) which comprises a front frame (602) of a thrust reverser structure of an aircraft nacelle and at least one cascade (603). The assembly is characterized in that, when the cascade is fixed to the frame, the axial distance (L) that separates the first blading (605) upstream of the cascade from a covering area (606) between the extension of the cascade and the front frame is greater than or equal to once the mean height (h) of the cascade.

Abstract: A thrust reverser for an aircraft bypass turbojet engine nacelle, this thrust reverser having a generally annular shape around an axis and including in particular flaps for deflecting the secondary flow through gratings, each of these flaps having a rigid wall and sealing elements located on the outer face of this wall, these sealing elements extending along side edges of the flap so as to provide a seal along these edges in the first position.

Abstract: A gripping head can be used for applying a patch to a surface to be draped. The gripping head for gripping a patch and applying the patch to a surface to be draped includes a suction chamber delimiting a suction sector and connected to a suction intake and a gripper connected to said suction chamber and comprising a piece of elastically deformable material configured to grip a patch under a gripping effect created in said suction chamber. The gripper includes selectively activatable gripping zones and the gripping head includes means for selectively activating the gripping zones.

Abstract: A method for manufacturing an acoustic panel including a first skin, a second skin and an intermediate structure enclosed between these skins and forming oblique cavities with respect to the latter. The method includes an intermediate polymerization step for fastening the intermediate structure to the first skin in order to increase the compressive strength thereof and in particular to support an automated operation of draping the second skin.

Abstract: The disclosure relates to a method for manufacturing an air intake lip comprising: the arrangement of a blank facing a three-dimensional forming surface of a die of a hydroforming tool, the forming of an air intake lip preform by hydroforming the blank on the three-dimensional surface of the die, the air intake lip preform having in section a U-shape, the outer wall of the air intake lip comprising at least one hollow housing with an inturned edge and a bottom, the housing having a shape corresponding to the shape of the at least one opening cavity, the cutting of an opening in each hollow housing keeping at least the inturned edge so as to obtain an air intake lip comprising at least one opening having an edge integrally formed with the outer wall of the lip.

Abstract: An acoustic assembly including a multicellular acoustic panel having at least one through cavity along a direction X, wherein the acoustic assembly further includes at least one sealing element including a body enclosing one or more acoustic cells, the body being able to be inserted into the cavity and extending along the direction X between a first face and a second face, the sealing element further including a seal on the second face of the body able to ensure the sealing with the acoustic panel.

Abstract: An acoustic panel for an aircraft turbomachine has a sandwich structure. The sandwich structure includes a cell structure with a plurality of acoustic cells, a perforated acoustic structure, and a porous acoustic structure attached to the perforated acoustic structure. The perforated acoustic structure is arranged between the cell structure and the porous acoustic structure. The porous acoustic structure is multi-layered and has a first woven textile layer and a second woven textile layer connected to the first layer. The second layer is arranged between the first layer and the perforated acoustic structure.

Abstract: The invention relates to an assembly structure (10) for manufacturing a composite part. The structure comprises:—a skin preform (Pp) and a generally omega-shaped stiffener preform (PT) each having first and second opposing surfaces, the stiffener preform extending along and opposite the first surface of the skin preform. longitudinally and transversely in the form of a stiffener preform cross-section,—a rigid skin tooling (Op) disposed opposite the entire second surface (Sp2) of the skin preform,—a local rigid stiffener tooling (Or1, Or2) extending transversely around the stiffener preform cross-section with a transverse dimension smaller than the transverse dimension of the first surface of the skin preform.

Abstract: A system for cooling a compartment for equipment in a nacelle having a member for drawing a cooling flow and a device for admitting the cooling flow into the compartment, having: a regulating member movably mounted with the ability to move in a first direction of movement limiting the admission when the internal pressure of the compartment is below the external pressure, and in a second direction of movement increasing the admission when the internal pressure is above the external pressure; a return member configured to keep the regulating member in a neutral open position and to damp the movement of the regulating member during modifications in the ratio of the pressures; a pressing member activated by a heat-sensitive element and configured to move the regulating number into a closed position so as to isolate the compartment in the event of fire.