An actuator system for actuating a movable structure of a thrust reverser, the system including a first motor, a first actuator driven by the first motor, a second actuator, and a first transmission shaft that is connected to the second actuator and to the first motor so that the second actuator is driven by the first motor, a second motor, a third actuator driven by the second motor, a fourth actuator, and a second transmission shaft that is connected to the fourth actuator and to the second motor so that the fourth actuator is driven by the second motor, and control means for controlling the motors to cause the first actuator, the second actuator, the third actuator, and the fourth actuator to be driven synchronously by the two motors. The invention also relates to a thrust reverser and to a jet engine fitted with such an actuator system.

The present disclosure provides a rear nacelle assembly for a turbojet having at least one thrust reversal device to redirect air circulating from upstream to downstream in a flow path of a turbojet and a mast that connects the nacelle to a structure of an aircraft. In one form, the thrust reverser device includes a cradle having a first longeron and a second longeron extending longitudinally opposite sides of the mast. The first and second longeron each include a device for slideably guiding the cowl and the cascade. In another form, a rear portion and a front portion of the cradle connects to the mast by a rear connecting device and front connecting device, respectively, such that the cradle is adapted to follow the movements of the turbojet.

A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and an deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.

A thrust reverser actuator system fitting and a v-blade may be coupled to a track beam. A portion of the load between a translating sleeve and a fan case may be transmitted through the track beam. The thrust reverser actuator system fitting may comprise an integral v-blade.

A thrust reverser for a gas turbine engine includes a frame, a first reverser door pivotally mounted to the frame, and a second reverser door pivotally mounted to the first reverser door.

A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.

The present disclosure relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle. The hydraulic control system includes devices for actuating and controlling the reverser having hydraulic locks and cylinders, the corresponding hydraulic solenoid valves, and sensors. The turbofan includes a full-authority electronic computer or aircraft having an avionics computer that gives reverse thrust commands. The system further includes an electronic concentration module, different from the computer, which concentrates the data relating to the operation of the reverser actuation and control devices. The module includes internal contact switches for controlling the solenoid valves, a device for monitoring the sensors, a device for analog or digital processing of the data, and a bus for communication with the computer.

An aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser includes cascades of mobile deflection vanes connected to cascade rails with a slideway connection that allows the cascades of vanes a translational movement between a cruising-flight position and a reverse-thrust position. The thrust reverser allows the cascade rails to be positioned in a forward position, in which the engine, the cascade rails and the deflection vanes can be removed from the propulsion assembly without the cascade rails colliding with the mobile cowl of the reverser. Dismantling and assembly or reassembly methods allow maintenance operations to be carried out on the engine thus dismantled.

Locking actuators for thrust reverser actuation systems, engines and aircraft including the same, and associated methods. A locking actuator includes an actuator housing, an extension element, and a lock assembly. The extension element is configured to translate along an actuator axis to transition between a retracted state and an extended state. The lock assembly transitions between a locked state and an unlocked state independent of transitioning the extension element between the retracted and extended states. In examples, a thrust reverser actuation system includes an actuator assembly with the locking actuator and a hydraulic control assembly. In examples, an engine includes a thrust generator, a nacelle, a transcowl, and the thrust reverser actuation system. In examples, a method of operating a thrust reverser actuation system includes transitioning a lock assembly from a locked state to an unlocked state and transitioning an extension element from a retracted state to an extended state.

A thrust reverser includes a diverter configured to divert at least a portion of an air flow from a nacelle and a cowl movable relative to an outer fixed structure of the thrust reverser. The thrust reverser further includes at least one rotatably hinged flap. The cowl configured to move from a closure position in which it provides aerodynamic continuity of the nacelle with the flap and covers the diverter. The flap is movable from a retracted position to an opening position in which it opens a passage in the nacelle and uncovers the diverter. The flap obstructs a portion of an annular channel of the nacelle when in the opening position. The thrust reverser also includes a cable-pulley system for driving the flap. The cable-pulley system includes at least one cable associated with at least one pulley to connect the flap to the thrust reverser.