Abstract: An aircraft propulsion assembly including at least one first support that supports an electric propulsion system, at least one first attachment configured to connect the first support and a support structure of an aircraft, at least one second support distinct from and dissociated from the first support supporting a source of electrical energy configured to supply the electric propulsion system with electrical energy, as well as at least one second attachment configured to connect the second support and the support structure. An aircraft may include at least one such propulsion assembly. Given that the second support is distinct from and dissociated from the first support system, vibrations generated by the electric propulsion system are not transmitted to the source of electrical energy.

Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Abstract: A propeller-type propulsion system for aircraft comprising a propeller, a plurality of electric motors and a gearbox. The gearbox has an output shaft onto which the propeller is mechanically coupled, and has an input shaft onto which the plurality of electric motors is mechanically coupled, the input shaft being off-center with respect to the output shaft. All of the electric motors are mechanically coupled one after the other along the input shaft such that the electric motors are at least partially integrated into a space, on the opposite side of the gearbox from the propeller, that is left free owing to the input shaft and the output shaft being off-center with respect to one another. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Abstract: A propeller-type propulsion system for aircraft, comprises a propeller, a plurality of electric motors comprising nested coaxial respective driveshafts, and a gearbox having an output shaft onto which the propeller is mechanically coupled, and an input shaft to which the coaxial driveshafts of the electric motors are mechanically coupled. As a result, the diameter of the propulsion system, in a plane perpendicular to the axis of rotation of the propeller, is reduced. This improves the aerodynamics and the fuel consumption of the aircraft.

Abstract: A propulsion unit, and an aircraft, with a propeller and electric motor, including at least one intermediate element interposed between the electric motor and the propeller and configured to transmit at least thrust loads generated by the propeller, a primary structure supporting the propulsion unit, at least one interface having: a first load path, configured to transmit loads perpendicular to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure, a second load path, configured to transmit loads that are parallel to the axis of rotation of the propeller, linking the at least one intermediate element to a support linked rigidly to or incorporated in the primary structure.

Abstract: A nacelle for a turbofan including a mobile cowl mobile in translation between a closing position and an opening position, a window on the upstream side by a fixed cowl and on the downstream side by the mobile cowl, and a reverser flap in rotation between a closed position and an open position. The nacelle includes a locking system with a groove fixed to the mobile cowl and extending between a first end and a second end, and a guided element mounted guided in the slide and fixed to the reverser flap, the guided element moving from the second end towards the first end with cowl movement and leaving the groove when the reverser flap begins rotation, and the guided element moving outside the groove while the reverser flap pivots from the positions and entering the groove at the end of rotation of the reverser flap.

Abstract: A nacelle comprising a fixed cowl and a movable cowl movable in translation, a window delimited by the fixed cowl and the movable cowl, a reverser flap movable in rotation and a drive mechanism coordinating the movements of the reverser flap with those of the movable cowl. The drive mechanism comprises two bearings fixed to the nacelle, for each bearing, a lever arm with one end movable in rotation on the bearing and one end articulated on the reverser flap, for each lever arm, a rail comprising a straight portion and a curved portion, for each lever arm, a rod with one end articulated on the lever arm, and for each rail, a slider that is movable in translation on the rail and is articulated to one end of the rod.

Abstract: A nacelle for a turbofan including a mobile cowl mobile in translation between a closing position and an opening position, a window on the upstream side by a fixed cowl and on the downstream side by the mobile cowl, and a reverser flap in rotation between a closed position and an open position. The nacelle includes a locking system with a groove fixed to the mobile cowl and extending between a first end and a second end, and a guided element mounted guided in the slide and fixed to the reverser flap, the guided element moving from the second end towards the first end with cowl movement and leaving the groove when the reverser flap begins rotation, and the guided element moving outside the groove while the reverser flap pivots from the positions and entering the groove at the end of rotation of the reverser flap.

Abstract: A nacelle comprising a fixed cowl and a movable cowl movable in translation, a window delimited by the fixed cowl and the movable cowl, a reverser flap movable in rotation and a drive mechanism coordinating the movements of the reverser flap with those of the movable cowl. The drive mechanism comprises two bearings fixed to the nacelle, for each bearing, a lever arm with one end movable in rotation on the bearing and one end articulated on the reverser flap, for each lever arm, a rail comprising a straight portion and a curved portion, for each lever arm, a rod with one end articulated on the lever arm, and for each rail, a slider that is movable in translation on the rail and is articulated to one end of the rod.

Abstract: A nacelle for a ducted fan turbojet engine comprising an engine. The nacelle comprises a fixed cowl, an upstream wall bounding off, with the engine, a working section for a secondary flow, a movable cowl with an interior wall and an exterior wall, and movable in translation between a closing position where the exterior wall adjoins the fixed cowl and the interior wall prolongs the upstream wall, and an opening position where the exterior wall is distant from the fixed cowl so as to open a window and the interior wall is distant from the upstream wall, an inverter flap between the interior wall and the exterior wall mounted to be free in rotation about an axis of rotation situated on the interior wall and a drive mechanism for moving the movable cowl.