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 aircraft nacelle air intake structure including an air intake lip with a U-shaped section to ensure air is shared between an inner face and an outer face. An acoustic panel is on the intake lip rear on the side of the inner face level with a first assembly point. An outer panel is on the intake lip rear on the side of the outer face level with a second assembly point. A front reinforcing frame on the intake lip inside is fixed to the air intake lip on the side of the inner face level with a first fixing point and on the side of the outer face level with a second fixing point. The length of the chord between the stop point and each fixing point is between ? and ? of the total chord between the stop point and the assembly point.

Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.

Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

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: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.

Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the inner shroud.

Abstract: A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations.

Abstract: A method for manufacturing deicing acoustic skin for an aircraft acoustic panel, using a fiber spacing device. The manufacturing method includes at least one step for manufacturing a layer assembly having a deicing layer supplied with electrically conductive fibers embedded in a resin and two insulating layers arranged on either side of the deicing layer, and a baking step. The method provides for fitting, during baking, a spacing device on the layer assembly, the spacing device having pins passing through said layer assembly, perforations being produced at the locations of the pins after the withdrawal of the spacing device, the fitting of the spacing device making it possible to produce perforations with desired sizes and shapes, in a simple and effective manner, and with a reduced manufacturing duration.

Abstract: An assembly including two juxtaposed acoustic panels. Resistive faces of the acoustic panels are in the continuation of one another. A first resistive face extends as far as the first end wall of a first panel. The first end wall is in contact with a second end wall of a second panel in the region of the first resistive face and of the second resistive face. A connecting piece is interposed between the first end wall and the second end wall over a part of the length thereof so that the connecting piece does not extend as far as the first and second resistive faces. That makes it possible to form an acoustic cladding that is continuous, exhibiting no non-acoustic zone or reduced-acoustic zone at the junction between the acoustic panels of which it is formed. A nacelle of an aircraft propulsion unit is one application.

Abstract: A method for manufacturing two soundproof panels of an aircraft nacelle including a duct. The manufacturing method includes a step of supplying a mold having, on a single face, a cavity for each soundproof panel, a step of producing, in the bottom of each cavity, an inner skin for being oriented towards the duct, and a curing step during which the elements present in the mold are cured in the mold. Such a method makes it possible to produce the two soundproof panels in the same mold, thus reducing the gaps between them after they have been positioned.

Abstract: A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.

Abstract: An air intake structure for an aircraft nacelle is disclosed. The air intake structure delimits a channel and includes a lip having a U-shaped cross section oriented towards the rear, a first sound-absorbing panel fixed behind the lip and delimiting the channel, and a second sound-absorbing panel fixed behind the first sound-absorbing panel and delimiting the channel. Each sound-absorbing panel includes a cellular core which is fixed between an inner skin pierced with holes and oriented towards the channel, and an outer skin oriented in the opposite direction, where the inner skin of the first sound-absorbing panel has a thickness greater than the thickness of the inner skin of the second sound-absorbing panel, and where each of the inner skins includes a heat source which is embedded in the mass of the inner skin.

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 production method for an acoustic panel comprising a step of producing a composite structure, a step of providing inserts, wherein each insert comprises a nozzle formed as a hollow cylinder with a through-bore and a cap comprising a base formed as a cylinder and a cover formed as a cone, and wherein the base is accommodated in the bore, a step of positioning the inserts in the composite structure by penetration of the cover into the composite structure so that the bore opens at one side and the other of the composite structure, a step of polymerizing during which the composite structure with the inserts is polymerized, a step of removing the caps, a first step of fixing a honeycomb structure to the polymerized composite structure, and a second step of fixing a rear skin to the honeycomb structure.

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 air intake structure for a nacelle of an aircraft is disclosed having an air intake lip with a U-shaped section open towards the rear, an acoustic panel that extends the air intake lip towards the rear and on an inner side, an outer panel extending the air intake lip towards the rear and on an outer side, and a rear strengthening frame fixed between the outer panel and the acoustic panel, where the rear strengthening frame partly defines an inner volume that is immediately in front of the rear strengthening frame. The air intake structure comprises an impact absorber element positioned in the inner volume and the impact absorber element assumes the form of a structure that is deformable during an impact and that is at least partially filled with a fluid. The impact absorber element is a flexible shroud filled with a pressurized gas.

Abstract: Sound attenuation panel for aircraft having a combination of acoustic attenuation properties. The acoustic panel includes an acoustic structure having a cellular structure and a resistive skin and a backing skin, the acoustic panel also including at least one auxiliary acoustic device with cavities that is configured to produce additional acoustic absorption, the auxiliary acoustic device with cavities being attached to the acoustic structure and including adjacent chambers or cavities separated by shared walls, each of the chambers or cavities having perforations and being adapted to produce acoustic absorption. The combination of the acoustic structure and the auxiliary acoustic device with cavities enables combination of the acoustic absorption properties of these two types of element and an increased range of frequencies of the noise that can be attenuated by the acoustic panel without increasing its overall size.

Abstract: An aircraft engine nacelle comprising an icing protection system and an icing protection method for such an aircraft engine nacelle. The aircraft engine nacelle comprises an air inlet comprising a lip, a tubular air inlet piece and an icing protection system. The icing protection system comprises an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip, a de-icing means powered by a second electrical energy source covering the tubular air inlet piece and a controller configured to acquire a current total air temperature value, and control the second electrical energy source as a function of the current total air temperature value.