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 aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.

Abstract: A forward part of an aircraft propulsion unit nacelle, comprising an air intake lip, an acoustic panel, and a rigid connection between the acoustic panel and the air intake lip. The acoustic panel has a resistive surface and a back skin, and the rigid connection is formed between the air intake lip and the back skin of the acoustic panel to form a propagation path for forces between the air intake lip and the back skin. This configuration gives freedom from design constraints, which enables an increase in the acoustic treatment region toward the front of the nacelle. An aircraft propulsion unit comprising a nacelle having such a forward part is also provided.

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. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a 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: An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.

Abstract: A forward part of an aircraft propulsion unit nacelle, comprising an air intake lip, an acoustic panel, and a rigid connection between the acoustic panel and the air intake lip. The acoustic panel has a resistive surface and a back skin, and the rigid connection is formed between the air intake lip and the back skin of the acoustic panel to form a propagation path for forces between the air intake lip and the back skin. This configuration gives freedom from design constraints, which enables an increase in the acoustic treatment region toward the front of the nacelle. An aircraft propulsion unit comprising a nacelle having such a forward part is also provided.

Abstract: A nacelle including a fixed structure, a central cover mounted on the fixed structure, a fan cover mounted on and articulated to the central cover between an open position and a closed position, and locking means that are distributed between each fan cover and the fixed structure and that are designed to assume a locked position in which they lock the fan cover to the fixed structure and an unlocked position in which they do not lock the fan cover to the fixed structure, in which the locked position can be adopted only when the fan cover is in the closed position, and in which the unlocked position can be adopted whether the fan cover is in the open or closed position and wherein the locking means are locked and unlocked by a rotation around a longitudinal axis of the nacelle.

Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.

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 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 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.