A nacelle forward part of an aircraft propulsion assembly, includes an air inlet lip at the front end, an internal structure and an external panel extending the lip, and an annular stiffening frame formed around an axis of revolution and comprising an internal peripheral edge linked to the internal structure and an external peripheral edge linked to the external panel. The stiffening frame presents an inclination relative to the axis of revolution, its slope being oriented towards the front end of the nacelle forward part. The stiffening frame is configured to deviate, outside the nacelle of the propulsion assembly, an object striking the stiffening frame. The stiffening frame so configured is capable of withstanding the impacts of objects without breaking while enabling the object striking the stiffening frame to be deviated towards the exterior of the nacelle.

Methods and systems for nacelle door electromechanical actuation may include a power distribution unit comprising a motor and differential gears; and a plurality of electromechanical actuators, each coupled to an output of a corresponding one of the differential gears. Each of the electromechanical actuators may include a configurable brake and a mechanical output, where the power distribution unit may provide mechanical torque to one of the electromechanical actuators via the motor and the differential gears based on configuration of the configurable brakes in each of the electromechanical actuators. At least one of the configurable brakes may be an electrically configurable brake. At least one of the configurable brakes may be a mechanically configurable brake. The differential gears may include two or more differential gears for receiving an input torque and supplying an output torque to one of a plurality of outputs of the differential gears.

A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

An aircraft fairing comprising at least one joint connecting a fixed panel to a movable panel, the joint comprising at least one first flange that is connected to the fixed panel, at least one second flange that is connected to the movable panel, and an elastically deformable junction region connecting the first and second flanges, the first and second flanges and the junction region forming a single part.

Embodiments of the invention are shown in the figures, where a nacelle cowling structure for a turbomachine having a bypass duct defining a path for an airflow is provided, the nacelle cowling structure including: an outer layer defining an external surface of the nacelle cowling structure, an inner layer defining a surface of the bypass duct, a front mounting area for fixation to the turbomachine and a rear mounting area for fixation to the turbomachine downstream the front mounting area with respect to the bypass duct flow path, wherein a space between the outer and inner layers and between the front and rear mounting areas is filled with acoustic material.

A propulsion assembly for an aircraft includes a pylon, a turbofan including a structure fixed to the pylon, and at least one thrust reverser, each having a top beam extending parallel to a longitudinal direction and mobile in rotation on the structure around a rotation axis parallel to the longitudinal direction. For each thrust reverser, an actuator is provided, a first end of which is articulated on the pylon and a second end of which is articulated on the top beam of the thrust reverser and the articulation axis of the actuator on the top beam is not coaxial with the rotation axis. Such assembly allows a positioning of the actuator in the upper part of the turbofan between the top beam of the thrust reverser and the pylon to free some space.

A propulsion assembly for an aircraft includes a pylon, a turbofan including a structure fixed to the pylon, and at least one thrust reverser, each having a top beam extending parallel to a longitudinal direction and mobile in rotation on the structure around a rotation axis parallel to the longitudinal direction. For each thrust reverser, an actuator is provided, a first end of which is articulated on the pylon and a second end of which is articulated on the top beam of the thrust reverser and the articulation axis of the actuator on the top beam is not coaxial with the rotation axis. Such assembly allows a positioning of the actuator in the upper part of the turbofan between the top beam of the thrust reverser and the pylon to free some space.

An electronic release system configured to unlock a hold open rod mechanism or latch mechanism includes an actuator interface configured with an input device and an actuator associated with the hold open rod mechanism or the latch mechanism. The input device configured to be actuated by personnel to initiate operation of an unlocking mechanism associated with the hold open rod mechanism or the latch mechanism. The electronic release system also includes a wiring assembly configured to connect the actuator interface to the actuator. The actuator interface configured to determine actuation of the input device and signal the actuator over the wiring assembly. The actuator being configured to operate the unlocking mechanism associated with the hold open rod mechanism or the latch mechanism.

A pivoting connection device connecting at least two components and comprising an end fitting having first and second branches, an arm positioned between the first and second branches of the end fitting, a cylindrical axle connecting the end fitting and the arm and having, at one of the ends thereof, a first portion configured to expand radially, a cylindrical rod configured to be screwed into a tapped portion of the cylindrical axle, an insert fitted on the cylindrical rod and movable between a first position, in which the first portion is not expanded, and a second position, in which the first portion is expanded radially, and a nut configured to be screwed on the cylindrical rod to urge the insert into the second position.

A nacelle for an aircraft engine comprising a first fan cowl and a second fan cowl, each fan cowl comprising a hinged end and a closing end, each fan cowl being mobile between a closed operating position and an open maintenance position, the first fan cowl having a larger angular coverage than the second fan cowl, the first fan cowl comprising an upper part connected to a lower part by an intermediate hinge so as to allow the lower part to fold towards the upper part.