Abstract: In a thrust reverser for an aircraft propulsion unit, the thrust reverser includes an internal fixed structure, a mobile cowl and blocking flaps. The thrust reverser also includes a first actuation mechanism that is configured to move the mobile cowl between a closing position and an opening position so as to cause the blocking flaps to move respectively between a retracted position and a deployed position, thus causing the thrust reverser to pass respectively between a full-thrust configuration and a thrust-reversal configuration. The thrust reverser also includes a second actuation mechanism that is configured to move the blocking flaps between the retracted position and a partially deployed position when the mobile cowl is in the closing position, so as to cause the thrust reverser to pass respectively between the full-thrust configuration and a reduced-thrust configuration.

Abstract: A sandwich panel for an aircraft turbojet nacelle includes an outer skin in contact with an air flow, an inner skin opposed to the outer skin, and an intermediate system comprising partitions connecting the inner and outer skins so as to form cells, the inner skin of at least one cell having at least one corrugation configured to allow the materials making up the sandwich panel to deform in the event of thermal variation.

Abstract: A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising: A standby protection device comprising a first connecting member fixedly mounted to the mast and a second connecting member fixedly mounted to the propulsion device, the second connecting member being rotatably hinged with respect to the first connecting member in at least one degree of freedom, and at least one retaining member keeping the second connecting member fixed with respect to the first connecting member, and configured, in the presence of a predetermined unbalance force on the propeller, to release the standby protection device in order to protect the mast.

Abstract: A thrust reverser including a stationary structure, a lower door and an upper door. This reverser includes at least one deflector configured to be able to redirect forward from the stationary structure a portion of fluid exiting the reverser according to a trajectory oriented towards a lateral opening extending between the stationary structure and the upper door. Such a deflector makes it possible to improve the control of the air current lines acting on a tail unit and in particular on a control surface of an aircraft equipped with such a reverser when the latter is in thrust reversal configuration, thereby making it possible to improve the controllability of this aircraft.

Abstract: A turbofan engine nacelle includes a thrust reverser system provided with at least one movable cowl retracting towards a rear reverse-jet position, tilting pivoting flaps which at least partially close an annular flow duct, and opening lateral openings of this annular flow duct equipped with reverser grids. Each movable cowl includes a control sector that slides in a transverse plane, a deflection device linking a fixed part of the nacelle to this control sector in order to make it slide towards a reversal position when the movable cowl retracts, and flap connecting rods linking this control sector to the pivoting flaps, which tilt these flaps, closing the annular flow duct, when the control sector slides towards its reversal position.

Abstract: A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.

Abstract: A seal interposed between a turbojet engine and a movable part of a nacelle includes a tubular body delimiting an inner cavity interposed between at least one fixing part and a platform. The platform includes a first lateral edge, a second lateral edge and a planar surface extending from the first lateral edge to the second lateral edge. The seal includes a protuberance arranged on the platform. The protuberance is centered on the platform or extends from the first lateral edge to the second lateral edge.

Abstract: A method for manufacturing a structural surface heat exchanger of preset or left-hand final shape for an aircraft includes the steps of forming, shaping and assembling, by welding or brazing, a first corrugated skin and a second smooth skin in order to obtain channels. Each channel is delimited by a corrugation of the first skin and the second smooth skin so as to form a structural surface heat exchanger of preset or left-hand final shape, wherein a fluid is configured to circulate in the channels and air is configured to circulate in contact with the second smooth skin.

Abstract: An aeronautical thrust reverser including a sliding cowl, shutter flaps and deflection cascades. The reverser includes, for each flap, a return member hinged to the sliding cowl, to a driving connecting rod itself hinged to a front frame of the reverser, and to a return connecting rod itself hinged to the flap, the latter being moreover hinged by its rear end to the sliding cowl. The return member, the driving connecting rod and the return connecting rod form an actuation system capable of opening the secondary flow duct in a direct thrust configuration.

Abstract: A propulsion unit for an aircraft includes a gas generator and an air intake with an upstream annular lip that is axially translatable. The propulsion unit further includes a sealing system of an annular shape that is borne by the lip at its downstream edge. The sealing system has an annular envelope with a downstream annular surface configured to bear on an upstream edge of the rest of the air intake. The sealing system also includes at least one elastically deformable member situated at the downstream edge of the lip and configured to be elastically deformed by compression and to exert an elastic return force on the envelope.

Abstract: A propulsion unit for an aircraft includes a gas generator; an air inlet; and a sealing system inserted axially between the air inlet and the gas generator. The sealing system has at least: a compression ring with a first axial end configured for mechanical connection to one of the gas generator and the air inlet. The compression ring also has a second opposite axial end configured to be axially separated from the other of the gas generator and the air inlet by an annular space. An annular seal is mounted in the space and configured to be axially compressed by reduction of the axial dimension of said space.

Abstract: The invention relates to a de-icing device for an air intake of an aircraft turbojet engine nacelle extending along an X-axis in which an air stream flows from upstream to downstream, the air intake having an inner cavity, extending annularly about the X-axis, which comprises an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the de-icing device comprising at least one injector for injecting a stream of hot air into the inner cavity, the injector comprising a nozzle extending along a nozzle axis, the nozzle being configured to inject a stream of hot air having a dissymmetry along the nozzle axis.

Abstract: A propulsion system for an aircraft, including at least one rotor and a nacelle cowling extending around the at least one rotor, said nacelle cowling being sectored and including at least one sector, which is fixed and sectors which are retractable in the peripheral direction relative to an axis of rotation of the rotor. The retractable sectors include at least a first series of sectors which are telescopically retractable in or on at least one fixed sector and at least a second series of sectors which are telescopically retractable in or on at least one fixed sector, the at least one fixed sector having an angular extent around the axis which is less than or equal to 90°.

Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: a pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, a speed reducer fixedly mounted inside the pipe along the longitudinal axis, at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.

Abstract: Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.

Abstract: A method for manufacturing annular sectors of an air intake lip includes arranging a revolution-shaped blank facing a three-dimensional forming surface of a die of a hydroforming tool, the three-dimensional surface including at least two plunging cavities spaced from each other along a circumferential direction, forming an air intake lip preform in one piece by hydroforming the revolution-shaped blank on the three-dimensional surface of the die, the air intake lip preform having in section a U-shape and including a plurality of crenellated portions each delimited by a plunging cavity, the production of a plurality of cutouts in the air intake lip preform so as to divide the preform into a plurality of annular sectors, each cutout including the removal of a sacrificial portion at the level of a crenellated portion so as to form two adjacent assembly edges with one of the two adjacent assembly edges including a plunging.

Abstract: An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.

Abstract: Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.

Abstract: An assembly includes a first part and a second part separate from the first part, the first and second parts being intended to be in frictional contact, the first part being made of an organic matrix composite material that has, on its surface, an abrasion-resistant area including a resin that contains polytetrafluoroethylene particles, the polytetrafluoroethylene particles being only present at the surface of the first part, and the second part being made of an organic matrix composite material and being in contact with the abrasion-resistant area of the first part.

Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.