A thrust reverser for an aircraft propulsion assembly includes a movable structure provided with external covers connected to hinges through a pivot connection allowing the external covers to rotate between a closed position and a maintenance position. The hinges are connected to secondary rails rigidly attached to an engine pylon through a sliding connection allowing the external covers to move in translation between a direct thrust position and a reverse thrust position. The hinges and the secondary rails are independent of beams to which the parts of the movable structure other than the external covers are connected. A method for maintaining an aircraft propulsion unit is also disclosed. The method includes positioning of the external covers in maintenance position followed by a placement of the beams and of the parts of the movable structure other than the external covers.

Symmetric cascade thrust reversers and related methods are disclosed. An example apparatus includes a first cascade and a second cascade, the first cascade and the second cascade to be radially spaced relative to a longitudinal axis of a first aircraft engine extending in a fore-aft direction, the first cascade to provide a first flow characteristic and the second cascade to provide a second flow characteristic, the first flow characteristic provided by the first cascade symmetric relative to the second flow characteristic of the second cascade with respect to a vertical plane passing through the longitudinal axis of the aircraft engine.

Symmetric cascade thrust reversers and related methods are disclosed. An example apparatus includes a first cascade and a second cascade, the first cascade and the second cascade to be radially spaced relative to a longitudinal axis of a first aircraft engine extending in a fore-aft direction, the first cascade to provide a first flow characteristic and the second cascade to provide a second flow characteristic, the first flow characteristic provided by the first cascade symmetric relative to the second flow characteristic of the second cascade with respect to a vertical plane passing through the longitudinal axis of the aircraft engine.

An air outlet for a nacelle for an aircraft turbofan having an inner wall and an outer wall connected to each other by a trailing edge, at least one radial through aperture extending over an angular portion of the air outlet and having inner and outer open faces and, for each aperture, a guiding device having inner and outer movable members movably mounted between a closed position wherein the inner and outer movable members respectively close off the inner and outer open faces, the aperture defining a closed cavity and an open position wherein the inner and outer movable members are configured to allow an external air flow to circulate in the aperture to support a reverse thrust phase.

An air outlet for a nacelle for an aircraft turbofan having an inner wall and an outer wall connected to each other by a trailing edge, at least one radial through aperture extending over an angular portion of the air outlet and having inner and outer open faces and, for each aperture, a guiding device having inner and outer movable members movably mounted between a closed position wherein the inner and outer movable members respectively close off the inner and outer open faces, the aperture defining a closed cavity and an open position wherein the inner and outer movable members are configured to allow an external air flow to circulate in the aperture to support a reverse thrust phase.

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.

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.

A thrust reverser system for a turbofan propulsion system of an aircraft includes a fixed structure and a translating structure configured to internally define a sequential flow path for air. The translating structure is slidable along an axial direction between a stowed position in which the translating structure is connected to the fixed structure, and an opening position in which the translating structure is spaced apart from the fixed structure in the axial direction to define a circumferential opening for outflow of air to external environment. An iris mechanism has a plurality of blades jointly movable between a rest configuration in which the blades jointly define a passage for air, and a deployed configuration in which the blades at least partially occlude a bypass duct of the turbofan propulsion system.

A thrust reverser system for a turbofan propulsion system of an aircraft includes a fixed structure and a translating structure configured to internally define a sequential flow path for air. The translating structure is slidable along an axial direction between a stowed position in which the translating structure is connected to the fixed structure, and an opening position in which the translating structure is spaced apart from the fixed structure in the axial direction to define a circumferential opening for outflow of air to external environment. An iris mechanism has a plurality of blades jointly movable between a rest configuration in which the blades jointly define a passage for air, and a deployed configuration in which the blades at least partially occlude a bypass duct of the turbofan propulsion system.

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.