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: A locking system for an aircraft nacelle is provided. The locking system includes a first portion configured to be mounted on a first part of an aircraft nacelle, and a second portion configured to be mounted on a second part of the aircraft nacelle. The locking system can be configured such that, when it is in the closed position, the first portion and the second portion are held together. The locking system further includes at least one buffer part and a load sensor joined together and configured to compress the load sensor between the buffer part and another part of the locking system when the locking system is in the closed position.

Abstract: An air ejection nozzle for a nacelle includes an outer aerodynamic line and an inner aerodynamic line meeting at a trailing edge. The air ejection nozzle includes at discrete positions at least one area of larger thickness that is compensated by at least one fairing to connect the aerodynamic lines to form the trailing edge. The fairing includes an outer wall and an inner wall delimiting a cavity therebetween. The inner wall provides for the continuity of the inner aerodynamic line, and the outer wall is solid and the inner wall is pierced so that the at least one fairing forms an acoustic attenuation structure.

Abstract: A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.

Abstract: A method for manufacturing annular sectors of an air intake lip includes arranging a revolution-shaped blank facing a three-dimensional forming surface of a die of a hydroforming tool, the three-dimensional surface including at least two plunging cavities spaced from each other along a circumferential direction, forming an air intake lip preform in one piece by hydroforming the revolution-shaped blank on the three-dimensional surface of the die, the air intake lip preform having in section a U-shape and including a plurality of crenellated portions each delimited by a plunging cavity, the production of a plurality of cutouts in the air intake lip preform so as to divide the preform into a plurality of annular sectors, each cutout including the removal of a sacrificial portion at the level of a crenellated portion so as to form two adjacent assembly edges with one of the two adjacent assembly edges including a plunging.

Abstract: A method for manufacturing annular sectors of an air intake lip includes arranging a revolution-shaped blank facing a three-dimensional forming surface of a die of a hydroforming tool, the three-dimensional surface including at least two plunging cavities spaced from each other along a circumferential direction, forming an air intake lip preform in one piece by hydroforming the revolution-shaped blank on the three-dimensional surface of the die, the air intake lip preform having in section a U-shape and including a plurality of crenellated portions each delimited by a plunging cavity, the production of a plurality of cutouts in the air intake lip preform so as to divide the preform into a plurality of annular sectors, each cutout including the removal of a sacrificial portion at the level of a crenellated portion so as to form two adjacent assembly edges with one of the two adjacent assembly edges including a plunging.

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: A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.

Abstract: A cascade-type thrust reverser includes a fixed structure on which a rear frame supporting cascades of vanes is mounted, a mobile structure having an outer wall, an inner wall formed in part by an acoustic panel, a partition connecting the outer wall to the acoustic panel, and actuators interposed between the fixed structure and the mobile structure. The actuators extend through orifices formed in the rear frame and the partition. In particular, the rear frame radially interferes with the acoustic panel when the mobile structure is in a direct-jet position.

Abstract: The invention relates to a grid-type thrust reverser comprising: a fixed structure (1) on which a rear frame (3) bearing said grids (5) is mounted; a mobile structure (7) comprising an outer wall (9), an inner wall (11) at least partially formed by at least one acoustic panel (13), and at least one partition (15) connecting the outer wall (9) to the acoustic panel (13); and actuators (16) placed between the fixed structure (1) and the mobile structure (7), extending through openings (17, 19) formed in the rear frame (3) and the partition (15). Said thrust reverser is characterised in that the rear frame (3) and the acoustic panel (13) are sufficiently radially close to each other to interfere mutually and in a controlled manner when said mobile structure (7) is in a direct jet position.