Abstract: An assembly including a nacelle element, such as a cover, a device for locking the nacelle element, a key for locking/unlocking the locking device and an indicator for indicating the position of the locking device. This assembly includes a control device which is configured to be actuated by the key when the key is withdrawn from the locking device so as to make the indicator move from a first state to a second state, the state of the indicator being representative of the locked or unlocked position of the locking device.

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: A laser projection method and device for drape-molding a part on a mold includes encoders to determine the theoretical position of calibration patterns according to a displacement of the mold such that a laser projector is automatically recalibrated when the mold is repositioned during the drape-molding operation.

Abstract: An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

Abstract: An active device for attenuating the acoustic emissions of an aircraft turbojet engine includes circulation conduits for a pressurized air flow rate supplying rotary elements each having a pulsation system for the delivered air. The rotary elements are controlled in amplitude and phase and deliver, to outlet diffusers, a pulsed air flow rate with a pulsation at the frequency of the noise to be attenuated having an amplitude and a phase adjusted according to a local feedback law with microphones to attenuate the radiated acoustic power.

Abstract: An acoustic attenuation panel includes a perforated acoustic wall, a first honeycomb structure coupled to the perforated acoustic wall and including a plurality of acoustic cells defined by peripheral partitions, a second honeycomb structure including a plurality of acoustic cells defined by peripheral partitions, and a septum which includes a plurality of macro-perforations and is positioned between the first honeycomb structure and the second honeycomb structure. Each acoustic cell of the first honeycomb structure and each acoustic cell of the at least second honeycomb structure are arranged opposite a single perforation of the septum.

Abstract: A nacelle for an aircraft turbojet engine includes a thrust-reversing device with a fixed structure and a movable structure translatably movable along an axis substantially parallel with a longitudinal axis of the nacelle between a retracted position in which it provides aerodynamic continuity with the fixed structure of the nacelle during operation of the nacelle with forward thrust and a deployed position in which it opens a passage intended for the circulation of a diverted secondary air flow during operation of the nacelle with reverse thrust. The nacelle includes at least one position sensor configured and arranged in the nacelle for detecting a deformation of the movable structure exceeding a permitted predetermined deformation threshold.

Abstract: An engine nacelle, for a turbojet engine of the type having a lubricant, includes a cooling system. The cooling system includes a cold source heat-exchanger, configured to exchange heat between a heat-transfer fluid and air, a heat-transfer fluid inlet duct leading into the cold source heat-exchanger, and a heat-transfer fluid outlet duct leading out of the cold source heat-exchanger. The inlet and outlet ducts are configured to form a recirculation loop between the cold source heat-exchanger and a hot source heat-exchanger, configured to exchange heat between the heat-transfer fluid and the lubricant. The cold source heat-exchanger is arranged on a movable surface of the nacelle with respect to the hot source heat-exchanger and the heat-transfer fluid inlet and outlet ducts are extendable and/or flexible to permit the relative movement between the cold source heat-exchanger and the hot source heat-exchanger.

Abstract: A thrust reverser includes a diverter configured to divert at least a portion of an air flow from a nacelle and a cowl movable relative to an outer fixed structure of the thrust reverser. The thrust reverser further includes at least one rotatably hinged flap. The cowl configured to move from a closure position in which it provides aerodynamic continuity of the nacelle with the flap and covers the diverter. The flap is movable from a retracted position to an opening position in which it opens a passage in the nacelle and uncovers the diverter. The flap obstructs a portion of an annular channel of the nacelle when in the opening position. The thrust reverser also includes a cable-pulley system for driving the flap. The cable-pulley system includes at least one cable associated with at least one pulley to connect the flap to the thrust reverser.

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 nacelle of an aircraft turbofan engine including an air inlet upstream from the engine, a median section configured to surround a fan of the engine and delimited on the outside by a fan cowl supported by a fan housing to which it is attached at the upstream portion, a downstream section delimiting an annular flow path in which the air is configured to flow and housing thrust reversal devices, the thrust reversal approach including a movable cowl associated with at least one actuator for moving the movable cowl between a direct jet position, in which it provides the aerodynamic continuity of the nacelle and an indirect jet position in which it opens up a passage in the nacelle by uncovering cascade vanes arranged around this flow path that receive the cold air flow to return it towards the outside and forwards, the cascade vanes being attached to the movable cowl.

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 testability method for the in-flight testing of an operating state of an electronic power chain having at least one power converter intended for driving an electric motor that actuates at least one aircraft component includes controlling actuation of the converter, transmitting a test signal, collecting at least one measurement signal, and determining an operating state.

Abstract: A propulsion unit for an aircraft including a nacelle with a D-shaped structure housing a thrust-reversing device with movable vanes, the nacelle containing two D-shaped half-structures each including an external reverser half-cowl. The propulsion unit contains an assembly box-type structure, attached in downstream cantilevered fashion to the turbojet engine fan casing, the box-type structure including two guide rails guiding the deflection vanes, a locking device between the assembly box-type structure and the half-beams in the six o'clock position of the D-shaped half-structures, the assembly box-type structure being arranged in the propulsion unit such that the guide rails guiding the vanes of the assembly box-type structure are situated in the continuation of the guide rails in the six o'clock position guiding the vanes attached to the fan casing, to provide continuity between the rails.

Abstract: A closing system that includes a closing actuator for doors of a thrust reverser, two sliding members, and a detection device. The closing actuator includes two first connecting rods. Each first connecting rod is configured to be connected to a first lateral edge of each door. The closing actuator is arranged to move each door at least towards the direct jet position. Each sliding member carries a second connecting rod configured to be connected to a second lateral edge of each door. The second connecting rods are arranged to be driven by the doors when the closing actuator moves the doors towards the direct jet position so as to displace the two sliding members. The detection device detects a defect of one of the first and second connecting rods. The detection device is configured to detect the relative position of the two sliding members in the direct jet position.

Abstract: A unit for handling an aircraft turbojet engine includes a frame, a front cradle and a rear cradle designed for supporting the turbojet engine, and a plurality of electric actuators. The cradles include devices for securing the turbojet engine. The plurality of electric actuators includes three electric actuators, where a first one and second one are arranged opposite each other, on either side of a longitudinal axis of the frame, connected to the front cradle and arranged for moving same in vertical translation, and where a third actuator is connected to the rear cradle and arranged for moving the same in vertical translation. The handling unit further includes a device for rotary driving of the front cradle about a longitudinal axis of the turbojet engine.

Abstract: A propulsion unit includes a nacelle, a turbojet engine, and a thrust reverser having gratings provided with movable thrust reversal gratings arranged around an annular duct for fresh air from the turbojet engine. The propulsion unit further includes actuators arranged around the annular duct and each actuator has a front end attached to the turbojet engine and a rear end which translates movable rear covers and gratings for opening, in the annular duct, radial passages which receive said gratings. The propulsion unit further has lifting points that are arranged around the annular duct for lifting the turbojet engine. At least one of the lifting points is formed on a beam for attaching an front end of an actuator.

Abstract: In a propulsion unit for an aircraft, including a nacelle and a turbojet engine supported by a pylon, a nacelle includes an outer shroud, a fixed internal structure defining, with the outer shroud, an annular space in which a cold air stream can circulate, and a sealing ring positioned between the fixed internal structure and the pylon. The sealing ring is used to separate a cold pylon zone from a hot engine zone. The propulsion unit includes a ventilation device allowing a portion of cold air of the cold air stream to be deviated to the sealing ring in order to ventilate the sealing ring.

Abstract: A thrust reverser for a turbojet engine nacelle includes thrust reversal cascade vanes arranged about an annular flow duct having a stationary front casing, at least one movable cover moving backwards into a thrust reversal open position, and tilting flaps connected by rear pivots to the movable cover, which, in an open position, tilt and thereby at least partially close the annular flow duct. The cascade vanes move backwards with the movable cover, in that, in the closed position, the tilting flaps and the cascade vanes are arranged outside the stationary casing, and each tilting flap is connected to the stationary casing by slides which cause the tilting flaps to tilt when the movable cover moves backwards.

Abstract: A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.