Abstract: A method for manufacturing an acoustic absorption structure comprising a plurality of acoustic elements, each of which is positioned in one of the cells of a cellular panel. The method includes a step of manufacturing acoustic elements provided with at least two radial tongues, a step of manufacturing a cellular panel provided with slots configured to accommodate the radial tongues of each acoustic element, a step of force-fitting each acoustic element in one of the cells of the cellular panel until the radial tongues are accommodated in the slots. An acoustic absorption structure obtained using this method is provided.

Abstract: A connection assembly between two portions of a line including an inner conduit for transporting a cryogenic fluid, the assembly including two flanges which are respectively arranged at the ends of the line portions and which are configured to be held in contact with one another by virtue of a fixing arrangement. The contact zone between the two flanges includes at least two grooves for positioning seals and at least one conduit opening out, for the one part, between the two seals and, for the other part, into an expansion chamber for the cryogenic fluid. The expansion chamber is arranged in one, or in the vicinity of one, of the first connection flange and the second connection flange. The expansion chamber includes a detector for detecting the presence of the cryogenic fluid in the expansion chamber or a recess configured for the installation of such a detector.

Abstract: An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.

Abstract: A fastening system for an aircraft configured to fasten at least one tank intended to contain liquid hydrogen includes a longitudinal box, an upper structure fastened to an upper side of the longitudinal box, a lower structure fastened to a lower side of the longitudinal box and at least two fastening frames including, on either side of the vertical plane of symmetry (P1), a fastening device for connecting a tank to the upper structure. The fastening system further includes at least two fastening devices for connecting a fastening point of the tank to the longitudinal box and at least two fastening devices for connecting a fastening point of the tank to the lower structure. The fastening system makes it possible to securely fasten at least one hydrogen tank on board an aircraft (AC).

Abstract: A soundproofing coating with a cellular structure having several structures connected in a transverse direction, each formed by connecting a first longitudinal strip with a second longitudinal strip. Each structure has, successively in the longitudinal direction, 1) a first cavity, the cross-section of which narrows gradually in the thickness of the coating until it closes, 2) a first connection of two walls, respectively of the first strip and the second strip, in contact with each other over part of the thickness of the coating, which provides a passage between the first cavity and a second cavity that thus form a Helmholtz resonator, 3) the second cavity, the cross-section of which gradually increases in the thickness of the coating and which is closed by a closing sheet, and 4) a second connection of two walls.

Abstract: A double-walled tank including at least one link system linking the outer and inner chambers of the tank and including a central part linked to the inner chamber and at least three blades distributed around the central part, each blade extending between a first end linked to the central part and a second end which has a head linked to the outer chamber, each blade being sufficiently flexible to be deformed elastically between its first and second ends in a direction of displacement.

Abstract: An aircraft having at least one transport pipe in which dihydrogen flows and, for each transport pipe, an embedding channel in which the transport pipe is housed. The embedding channel has a gutter that has a bottom and an opening opposite the bottom and a cover that covers the opening of the gutter. The cover constitutes an outer wall of the aircraft in direct contact with external air surrounding the aircraft. The cover has ventilation windows passing through it that allow the passage of the dihydrogen towards the outside. With such an arrangement, even in the event of dihydrogen leaking into the embedding channel, the dihydrogen is automatically evacuated towards the outside of the aircraft.

Abstract: An aircraft having a systems cabinet positioned in an avionics bay to the rear of a landing gear compartment and connected to the fuselage by at least one lower connecting system. The systems cabinet and/or the lower connecting system comprises at least one longitudinal beam, which has a front end connected by a front connection to a wall separating the avionics bay and the landing gear compartment, the front connection comprising a sliding connection sliding in a direction substantially parallel to the longitudinal axis.

Abstract: An aircraft including at least one system rack positioned under a floor and including a series of vertical first uprights, distributed in a direction parallel to the longitudinal axis of the aircraft. The aircraft includes at least a first upper connecting system connecting at least one of the first uprights and a rail of the floor oriented parallel to the longitudinal axis. In so far as the first uprights of the system rack are not connected to the crossbeams of the floor, they can be positioned irrespective of the position of the crossbeams, and this contributes to simplifying the design of the system racks and allows these to be standardized.

Abstract: An aircraft including at least one hydrogen engine, at least one hydrogen supply device including at least one hydrogen tank and at least one item of equipment through which the hydrogen flows and which is positioned between the hydrogen tank and the hydrogen engine. The aircraft includes at least one sealed container sealed from the outside air, in which sealed container the equipment of the hydrogen supply device is positioned. This solution allows a safe hydrogen installation to be obtained using existing equipment.

Abstract: A connection assembly between two portions of a supply line for a cryogenic fluid, the assembly including a male nozzle arranged to be at least partially inserted into a female nozzle together forming a tight mechanical link, over a distance of a few centimeters, a thermal insulation chamber for each of the two line portions and an additional thermal insulation chamber to thermally insulate the connection zone of the two line portions, and an expansion chamber for the cryogenic fluid that is configured to be linked to a cryogenic fluid sensor, arranged about the connection zone of the two line portions. This enables two cryogenic fluid line portions to be connected without requiring one portion to be inserted into the other portion over a significant length, thereby enhancing mechanical flexibility and obviating the need for significant free space about the connection assembly to assemble and disassemble the assembly.

Abstract: A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.

Abstract: An auxiliary power unit for an aircraft. It includes an air compressor coupled to an air-drawing device for drawing in air from outside the aircraft, the compressor supplying compressed air to a manifold. The manifold is configured to supply air to an environmental control system and a start-up module of at least one propulsion system of the aircraft running on hydrogen. The manifold is also configured to supply air to a fuel cell stack arranged to provide an electric generation function configured to power non-propulsive systems of the aircraft, the fuel cell stack also being supplied with hydrogen from a tank supplying hydrogen to the at least one propulsion system of the aircraft.

Abstract: A door for a thrust reversal system, an aircraft with such a door, and a method for manufacturing a door of a thrust reversal system. The door comprises a wall formed from long fibers embedded in a thermoplastic resin matrix and a network of ribs overmolded on one of the faces of the wall. A propulsion assembly of an aircraft comprises a thrust reversal system having a plurality of such doors.

Abstract: An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

Abstract: This control system takes into account the thermomechanical aspects of materials to quickly and easily determine optimal cutting conditions and to automatically control machining to preserve the integrity of the workpiece. This system includes an acquisition module configured to acquire values of a set of input parameters relating to cutting conditions and material properties of the piece, and a microprocessor configured for determining at least one operating cutting parameter representative of a cutting signal from the machining apparatus using a set of output parameters of an integrity model previously constructed during a learning phase. The integrity model connects the set of input parameters to the set of output parameters comprising specific cutting coefficients representative of the material integrity of the piece, and establishes at least one fatigue threshold of the at least one cutting operating parameter. The fatigue threshold allows control of the progress of cutting operations.

Abstract: An aircraft including a first electrical distribution busbar and a second electrical distribution busbar extending at least in part in a fuselage of the aircraft, in a longitudinal direction of the fuselage. A first electric generator is connected to the distribution conductors of the first electrical distribution busbar via a first coupling switch directly connected to the first electric generator and to the distribution conductors of the first busbar. A second electric generator is connected to the distribution conductors of the second electrical distribution busbar via a second coupling switch directly connected to the second electric generator and to the distribution conductors of the second busbar. The first coupling switch and the second coupling switch are positioned in the aircraft independently of one another.

Abstract: A system for assisting the maintenance of an aircraft is configured for implementing the following steps in an iterative manner determining a spectral power density of the position of a control surface over a time window; when the spectral power density corresponds to an amplitude of oscillations of the control surface upwardly crossing this predetermined threshold, storing an excess amplitude start time; and when the spectral power density corresponds to an amplitude of oscillations of the control surface downwardly crossing this predetermined threshold: determining a time interval between the excess amplitude start time and an excess amplitude end time, during which the amplitude of oscillations of the control surface has remained above the predetermined threshold; and determining an indicator representative of the energy corresponding to these oscillations during the time interval.

Abstract: An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

Abstract: A turbofan with a nacelle having a fixed structure, a mobile assembly bearing second blocking element and able to move between an advanced position and a withdrawn position, a set of deflectors able to move in translation between an advanced position and a withdrawn position, and an actuation system having a carriage, a blocking lever bearing first attachment element and able to move between a blocking position and a free position, and a transmission system configured to move the blocking lever from the blocking position to the free position when the mobile assembly reaches a tilting position between the advanced position and the withdrawn position.