Abstract: A nacelle for an aircraft turbojet engine includes a thrust-reversing device with a fixed structure and a movable structure translatably movable along an axis substantially parallel with a longitudinal axis of the nacelle between a retracted position in which it provides aerodynamic continuity with the fixed structure of the nacelle during operation of the nacelle with forward thrust and a deployed position in which it opens a passage intended for the circulation of a diverted secondary air flow during operation of the nacelle with reverse thrust. The nacelle includes at least one position sensor configured and arranged in the nacelle for detecting a deformation of the movable structure exceeding a permitted predetermined deformation threshold.

Abstract: A nacelle for an aircraft turbojet engine includes a thrust-reversing device with a fixed structure and a movable structure translatably movable along an axis substantially parallel with a longitudinal axis of the nacelle between a retracted position in which it provides aerodynamic continuity with the fixed structure of the nacelle during operation of the nacelle with forward thrust and a deployed position in which it opens a passage intended for the circulation of a diverted secondary air flow during operation of the nacelle with reverse thrust. The nacelle includes at least one position sensor configured and arranged in the nacelle for detecting a deformation of the movable structure exceeding a permitted predetermined deformation threshold.

Abstract: The present disclosure relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a tranverse pivot in order to partially close off the air stream so as to guide it forwards, further including locks for locking the flaps in an intermediate opening position, between the closed position and the open position.

Abstract: An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.

Abstract: A thrust reverser for a nacelle of an aircraft turbojet engine includes at least one movable thrust reverser cowl, a means for locking the cowl, a variable section outlet nozzle, and at least one actuator including an actuator rod. The thrust reverser is provided with a resilient coupler comprising a body which is rigidly connected to the thrust reverser cowl and a resilient return and abutment device that engages with the actuating rod of the actuator such as to resiliently return the nozzle to a neutral position. The return device is calibrated such that, when the cowl is unlocked, the return device opposes the relative movement of the actuating rod relative to the cowl, such as to enable the movement of the cowl and the nozzle, and when the cover is locked, the actuator drives the actuating rod against the return device to enable the movement of the nozzle.

Abstract: A thrust reverser for a nacelle of an aircraft turbojet engine includes at least one movable thrust reverser cowl, a means for locking the cowl, a variable section outlet nozzle, and at least one actuator including an actuator rod. The thrust reverser is provided with a resilient coupler comprising a body which is rigidly connected to the thrust reverser cowl and a resilient return and abutment device that engages with the actuating rod of the actuator such as to resiliently return the nozzle to a neutral position. The return device is calibrated such that, when the cowl is unlocked, the return device opposes the relative movement of the actuating rod relative to the cowl, such as to enable the movement of the cowl and the nozzle, and when the cover is locked, the actuator drives the actuating rod against the return device to enable the movement of the nozzle.

Abstract: A tertiary locking assembly for a thrust reverser includes a tertiary lock, a primary control line associated with the tertiary lock, and a secondary control line. The primary control line includes a primary electromechanical valve and a primary power supply line connected to the primary electromechanical valve. In addition, the secondary control line has a secondary electromechanical control valve and a secondary power supply line connected to the secondary electromechanical control valve. In particular, the secondary control line is provided with at least one manually controlled switch.

Abstract: The present disclosure concerns thrust reversers for a nacelle of a turbojet engine having a sliding cover. The active lock is rigidly connected to a fixed structure and engages with a locking interface of a mobile structure by a tilting bolt driven by a controlled electric motor. The tilting bolt is tiltably mounted with a pusher to push the mobile structure away from the fixed structure during the deployment of the mobile structure relative to the fixed structure driven by the controlled electric motor via mobilizing the active lock according to a predefined sequence of movements of the tilting bolt or the pusher.

Abstract: An aircraft propulsion assembly including a turbojet nacelle, and the nacelle includes a stationary structure and a movable structure. The movable structure includes: a thrust reversal device including a cowl translatable along a substantially longitudinal axis of the nacelle between a retracted position, and a deployed position; and a secondary air flow exhaust nozzle including a device for electrically controlling and actuating the nozzle. In particular, the device for controlling and actuating the nozzle includes an electrical switch suitable for being closed during a direct jet operation of the nacelle and moreover suitable for being open during a reverse jet operation. The electrical switch includes a stationary connector and a movable connector.

Abstract: An actuator for an aircraft turbine engine nacelle with a one-piece annular rear part, includes an engine assembly having a nut which is capable of rotating but not of translational movement, and a shaft for turning this nut. The actuator also includes a screw assembly having a screw capable of translational movement without rotating, in mesh with the nut, and a ball joint at one end of this screw intended to be fixed to the annular rear part.

Abstract: A tertiary locking assembly for a thrust reverser includes a tertiary lock, a primary control line associated with the tertiary lock, and a secondary control line. The primary control line includes a primary electromechanical valve and a primary power supply line connected to the primary electromechanical valve. In addition, the secondary control line has a secondary electromechanical control valve and a secondary power supply line connected to the secondary electromechanical control valve. In particular, the secondary control line is provided with at least one manually controlled switch.