Abstract: An aircraft nacelle comprising an air inlet, with a single fan cowling made of a single piece which extends over all the circumference of the fan. The fan cowling is borne by the air inlet and is mounted to be rotationally mobile about the axis of the nacelle relative to the air inlet, via a link and guiding arrangement comprising a circular rail and a runner capable of sliding along the circular rail. The fan cowling comprises one or more openings closed by hatches allowing access to the interior of the nacelle. The fan cowling has little susceptibility to being deformed both in flight and on the ground during maintenance operations. Furthermore, no pylon portion is needed in the zone of the fan cowling since the latter is not attached to the pylon.

Abstract: An engine assembly comprising an engine and a pod surrounding the engine that is equipped, upstream according to the direction of entry of air into the engine, with a fan provided with blades, the pod having an upstream air intake. The engine assembly also comprises a display unit including at least one light ring arranged in the air intake upstream of the fan, the light ring including at least one row of light-emitting diodes and being configured to emit at least one light beam and to project it on the blades of the fan.

Abstract: An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.

Abstract: A frost protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel and an air intake lip forming a leading edge of the nacelle. The protection system comprises a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the at least one acoustic panel.

Abstract: An aircraft engine air inlet lip takes an annular form about a longitudinal axis and delimits an air inlet stream, and includes: a wall having a U-shaped profile having an outer face oriented towards outside of the air inlet lip and an inner face oriented towards interior of the air inlet lip, an inner wall extending inside the wall between two zones of the inner face, so as to close an inner chamber delimited between the wall and the inner wall and filled with a gas, the inner wall having an upstream face oriented towards and a downstream face oriented away from the inner chamber, a fan configured to move the gas contained in the inner chamber, and at least one pipeline fixed to the upstream face and extending all around the air inlet lip and configured to be fed with a heat transfer fluid heated by a heat source.

Abstract: The invention relates to a wall made from a composite material comprising at least two layers of fibers (18, 18?) embedded in a resin matrix, a crack being able to spread in said wall in a direction of propagation, characterized in that it comprises at least one longilineal metal reinforcement (20), oriented in a direction secant to the direction of propagation, inserted between two layers of fibers (18, 18?) of the wall.

Abstract: An acoustic treatment panel in which each cell includes a plurality of conduits which extend from the porous acoustically resistive structure to the reflective layer of the acoustic treatment panel, each conduit including at least one opening set away from the porous acoustically resistive structure and configured to cause the inside and the outside of the conduit to communicate.

Abstract: An acoustic treatment panel including a porous acoustically resistive structure which includes at least one external layer which is in contact with the external environment and which has through holes, internal strips including several openings which communicate with the inside of the cells of the panel and connecting canals, interposed between the external layer and the internal strips, which ensure that the floor-section openings communicate with at least one through hole of the external layer.

Abstract: An air intake structure for an aircraft nacelle including an air intake lip with a U-shaped cross section which is open towards the rear, with a rear end, an acoustic panel including an inner wall, wherein the air intake lip has at a rear end a contact surface oriented towards the inside of the air intake lip, in that the contact surface takes the shape of a bevel which points towards the rear and against which the inner wall is placed, in that at the point of the bevel, the inner wall runs on from the air intake lip and in that level with the contact surface, the air intake lip is fixed to the inner wall by first fasteners. The bevelled shape restricts the possibility of dust and water being halted in their progress and blocking up the air intake structure as a result.

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: A structure establishing a sound insulator and including a first plate, a second plate having holes therethrough, and a web stuck between the plates. The web includes a plurality of intermediate strips perpendicular at least to one of the plates, a plurality of folded strips which are folded in a zig-zag formation, each folded strip being arranged between two successive intermediate strips, and establishes, with the intermediate strips, triangular prisms, where, for two folded strips on either side of a same intermediate strip, the generator of the triangular prism of one of the folded strips forms an acute angle with respect to the first plate, and the generator of the triangular prism of the other folded strip forms an obtuse angle with respect to the first plate.

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. Thus, the air input lip has a lighter structure.

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: 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 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.

Abstract: An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.

Abstract: An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a power plant. The two ducts are arranged end-to-end and connected by a connection. The connection comprises a bracket which extends between a first region for connecting to the power plant and a second region for connecting to the air intake, and which comprises a J-shaped profile in longitudinal planes, having at least one curved portion offset towards the outside of the nacelle with respect to the connecting regions.

Abstract: A process for the production of an acoustic treatment panel that includes an acoustically resistive layer (24), at least one alveolar structure (26), and a reflective layer (28), as well as at least one channel that is bordered at least in part by a wall (32) that is secant with at least one wall of a cell of the alveolar structure (26), includes elevating the temperature of the wall (32) and the ends of the cells of the alveolar structure (26) and injecting a pressurized gas into the channel (30) so as to expand the wall (32) of the channel so as to flatten it against the ends of the cells of the alveolar structure (26) in such a way as to produce a weld by continuous diffusion between the ends of the walls of the cells of the alveolar structure (26) and the wall (32) of the channel (30).

Abstract: An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.

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.