Abstract: A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

Abstract: An aircraft propulsion system comprising a propeller, a plurality of electric motors, a transmission system configured to couple the electric motors to the propeller, and a propeller pitch adjustment system positioned at the rear of the transmission system. At least one of the electric motors is positioned in front of the transmission system. A connection structure is interposed between the propeller and the transmission system, the connection structure and the output shaft of the transmission system connected to the propeller being configured so that no electric motor positioned in front of the transmission system interferes with the propeller. Also an aircraft with such a system.

Abstract: A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

Abstract: An anterior part of a nacelle of a propulsion assembly of an aircraft, having an air intake lip and a front frame disposed at the rear of the air intake lip that connects an outer part to an inner part of the air intake lip. A de-icing duct is formed in front of the front frame. The front frame is shaped so that the de-icing duct has a main cavity and a thermal transition region formed behind the main cavity between an internal face of the outer part of the air intake lip and the front frame. The thermal transition region extends over a longitudinal dimension greater than its average radial dimension, the front frame forming, with respect to the internal face of the outer part of the air intake lip, an angle, measured longitudinally, of between ?20° and +10° over the majority of the thermal transition region.

Abstract: An anterior part of an aircraft propulsion assembly nacelle, having an air intake lip disposed at a front end and an outer panel, of which an outer face extends an outer part of the air intake lip. A front edge of the outer panel and a rear edge of the air intake lip are shaped so as to overlap radially and to nest so as to ensure a continuous surface between the outer surface of the outer part of the air intake lip and the outer face of the outer panel. Moreover, the front edge of the outer panel is connected to the rear edge of the air intake lip with no added rigid element. This permits a rigid connection while avoiding creating local irregularities on the outer surface of the nacelle, which irregularities might disrupt the flow of air around the nacelle, giving rise to additional drag.

Abstract: 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.

Abstract: An aircraft nacelle including a conduit rigidly connected to an air inlet and a conduit rigidly connected to an engine, a link between the conduit rigidly connected to the air inlet and the conduit rigidly connected to the engine. The link includes a sleeve that receives one end of a first conduit and is rigidly connected to a second conduit, and linking elements that link the sleeve and the first conduit and that are distributed about the entire circumference of the nacelle, each linking element having a threaded stem oriented in a radial direction and being configured to enable tightening from inside the first conduit.

Abstract: An anterior part of a nacelle of an aircraft propulsion unit having an air inlet lip at the front end, an internal structure and an external panel extending the air inlet lip, and an annular rigidifying frame having an external peripheral edge connected to the external panel is disclosed. The anterior part of the nacelle includes a shock-absorbing element connected rigidly on the one hand to an internal peripheral edge of the rigidifying frame and on the other hand to the internal structure.

Abstract: An anterior part of a nacelle of a propulsion assembly of an aircraft, having an air intake lip and a front frame disposed at the rear of the air intake lip that connects an outer part to an inner part of the air intake lip. A de-icing duct is formed in front of the front frame. The front frame is shaped so that the de-icing duct has a main cavity and a thermal transition region formed behind the main cavity between an internal face of the outer part of the air intake lip and the front frame. The thermal transition region extends over a longitudinal dimension greater than its average radial dimension, the front frame forming, with respect to the internal face of the outer part of the air intake lip, an angle, measured longitudinally, of between ?20° and +10° over the majority of the thermal transition region.

Abstract: An anterior part of an aircraft propulsion assembly nacelle, having an air intake lip disposed at a front end and an outer panel, of which an outer face extends an outer part of the air intake lip. A front edge of the outer panel and a rear edge of the air intake lip are shaped so as to overlap radially and to nest so as to ensure a continuous surface between the outer surface of the outer part of the air intake lip and the outer face of the outer panel. Moreover, the front edge of the outer panel is connected to the rear edge of the air intake lip with no added rigid element. This permits a rigid connection while avoiding creating local irregularities on the outer surface of the nacelle, which irregularities might disrupt the flow of air around the nacelle, giving rise to additional drag.

Abstract: An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.

Abstract: A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

Abstract: 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.

Abstract: An anterior part of a nacelle of an aircraft propulsion unit having an air inlet lip at the front end, an internal structure and an external panel extending the air inlet lip, and an annular rigidifying frame having an external peripheral edge connected to the external panel is disclosed. The anterior part of the nacelle includes a shock-absorbing element connected rigidly on the one hand to an internal peripheral edge of the rigidifying frame and on the other hand to the internal structure.

Abstract: A cabin space dedicated to passengers and, beneath said cabin space, an under-cabin space which extends along the longitudinal axis of said aircraft. The under-cabin space comprises, distributed along two lines parallel to the longitudinal axis of the aircraft, two sets of systems which are able to carry out functions necessary for the operation of the aircraft. The two lines of sets of systems are disposed respectively in two lateral zones of the under-cabin space which are spaced apart transversely from one another and enclose a free central zone which extends along the longitudinal axis of the aircraft. This arrangement thus eliminates any technical zone from the under-cabin space, thereby facilitating the internal layout and maintenance.

Abstract: An aircraft nacelle including a conduit rigidly connected to an air inlet and a conduit rigidly connected to an engine, a link between the conduit rigidly connected to the air inlet and the conduit rigidly connected to the engine. The link includes a sleeve that receives one end of a first conduit and is rigidly connected to a second conduit, and linking elements that link the sleeve and the first conduit and that are distributed about the entire circumference of the nacelle, each linking element having a threaded stem oriented in a radial direction and being configured to enable tightening from inside the first conduit.

Abstract: A cabin space dedicated to passengers and, beneath said cabin space, an under-cabin space which extends along the longitudinal axis of said aircraft. The under-cabin space comprises, distributed along two lines parallel to the longitudinal axis of the aircraft, two sets of systems which are able to carry out functions necessary for the operation of the aircraft. The two lines of sets of systems are disposed respectively in two lateral zones of the under-cabin space which are spaced apart transversely from one another and enclose a free central zone which extends along the longitudinal axis of the aircraft. This arrangement thus eliminates any technical zone from the under-cabin space, thereby facilitating the internal layout and maintenance.

Abstract: A device and method for assembling two structural elements made from a composite material is provided. The device includes two cylindrical flanged receptacles, each pierced by an aperture perpendicular to the axis of the cylinder, and a shaft that can be introduced into said apertures. The device also includes bearing means, which bear on the interior surfaces of the cylindrical receptacles and can maintain tension in the shaft when the shaft extends through the apertures in the two receptacles. The device includes means of placing the shaft under tension.

Abstract: According to the invention, the horizontal stabilizer comprises a fixed intermediate part secured to the structure of said aircraft and at least one mobile edge part able to slide with respect to said fixed intermediate part, transversely to the length thereof. Mobile flaps are able to provide the aerodynamic continuity of the suction face and of the pressure face of said stabilizer when said mobile edge part is deployed.

Abstract: According to the invention, the horizontal stabilizer comprises a fixed intermediate part secured to the structure of said aircraft and at least one mobile edge part able to slide with respect to said fixed intermediate part, transversely to the length thereof. Mobile flaps are able to provide the aerodynamic continuity of the suction face and of the pressure face of said stabilizer when said mobile edge part is deployed.