Abstract: A method for skeletonizing the strands of a composite material part in a 3D image having a step of detecting oriented section centers of the strands and a link from each center to the closest center having the same orientation, the detection being carried out by means of at least one reference volume having an oriented centered strand pattern, the detection step having, for each reference volume: •a step of determining portions of the image, •a step of calculating a correlation score between the reference volume and each portion associated with the central voxel of each portion, so as to obtain a correlation score for each voxel of the image; and •a step of determining the strand centers corresponding to the voxels having a correlation score which corresponds to a local maximum.

Abstract: A device, for non-destructive testing of a mechanical part made of a polycrystalline material, includes: an ultrasonic probe including a two-dimensional array of transducers capable of emitting and receiving signals at different excitation angles; and a processing module suitable for controlling the emission and the reception of the transducers, for processing the signals received by the transducers so as to express the signals received by the ultrasonic probe in two planar wave planes constructed from the emission and reception wave vectors of the probe, and for deducing therefrom information representative of the three-dimensional orientation of the fiber structure of the mechanical part.

Abstract: A machine for automatically draping and compacting including a draping head that grasps, deposits and compacts fiber plies on a draping support, the draping head including first and second rigid supports and a gripper including a piece of elastically deformable material having a face to grasp a ply and intended to bear against a draping support surface. The first and second supports are connected to, respectively, a robotic handling device and to the first support and to the gripper. The draping head includes bearing force or pressure measuring elements between the first and second supports or housed in the first support. A control unit is connected to the bearing force or pressure measuring elements to monitor a compaction bearing force or pressure applied by the draping head.

Abstract: A method for transferring an adhesive onto a part intended to be glued on a carrier, the adhesive being in the form of a double-sided film including a separator on each face, the part including an internal concave portion that does not enable uniform application of the adhesive film once the separators have been removed. The method includes attaching the adhesive film to a punch that matches the shape of the part within a range that approximately corresponds to the thickness of the adhesive film; removing the separator from the side of the adhesive film that is to be attached to the part; setting the part on the punch covered with the adhesive film that has had its separator removed; and transferring the adhesive film onto the part by creating a vacuum between the part and the punch by means of a vacuum device.

Abstract: The invention relates to a device for connecting parts of an aircraft engine. The connection device comprises connectors suitable for connecting a first and a second part so as to establish a physical transfer link between these parts and means which enable it to monitor the state of the connection in particular by means of an impedance measurement carried out in a circuit formed by components integrated into said connectors.

Abstract: An aircraft cabin is provided. The aircraft cabin comprises a first seat unit and a second seat unit, the first and second seat units being in a first row of seat units and being separated by an aisle. The cabin comprises a partition movable between a stowed position and a deployed position in which the partition is positioned at least partially in the aisle between the first and second seat units thereby at least partially blocking the aisle. The cabin further comprises an item of furniture movable between a stowed position and a deployed position in which the item of furniture is positioned in the aisle between the first and second seat units.

Abstract: An assembly for producing a molding, made of removable material, of a turbomachine blade, includes an injection mold for the removable material in which a first core element and a second core element are mounted in a predetermined molding position, wherein the first and second core elements extend in a first direction. The mold includes a first face for molding a pressure-side face of the blade and a second face for molding a suction-side face of the blade and arranged facing the first face in a second direction perpendicular to the first direction. Retaining members hold the cores in position in the injection mold.

Abstract: A method for manufacturing a flame tube for a turbomachine, the flame tube extending about an axis and comprising an annular radially internal wall and an annular radially external wall, connected to each other by an end wall or head wall, the internal wall, the external wall and the end wall defining an internal volume, at least one part of the said end wall forming a double wall comprising a first part and a second part connected to each other and spaced apart from each other so as to delimit a flow channel for a flow of cooling air opening into the said internal volume, the said flow channel comprising at least one air-inlet opening, the first and second parts of the double wall being connected by connecting zones or bridges extending into the flow channel for the cooling-air flow, the flame tube being manufactured by additive manufacturing.

Abstract: A method for manufacturing a coating for a porous substrate, and to a mechanical part equipped with such a coating, the method including the following steps: providing a substrate to be protected, the substrate containing pores; providing a liquid suspension containing at least a first powder and a second powder, the first powder possessing a D50 strictly smaller than that of the second powder and an electrophoretic mobility strictly higher than that of the second powder; providing a DC electric generator; placing the substrate in the suspension, as a first electrode, and connecting the substrate to a first terminal of the electric generator; placing a second electrode in the suspension and connecting the second electrode to a second terminal of the electric generator; and applying a continuous or pulsed voltage of at least 10 V across the two electrodes for at least 1 minute.

Abstract: A suspension assembly for a turbine engine includes a beam that attaches to an aircraft pylon. The beam has first and second portions, each carrying a half-housing together defining a ball joint housing. A ball joint nut is hingedly engaged to rotate in the ball joint housing, and a cylindrical part is configured to be attached to a fixed portion of the turbine engine, hinged in the ball joint housing, and mounted so as to be pivotable about its axis in the ball joint nut. The suspension assembly further includes a support ring surrounding the two half-housings around their entire circumference. The support ring performs a safety function in the event of failure of at least one element of the suspension assembly.

Abstract: A hydraulic torque measurement device for an aircraft engine unit includes a hermetically sealed enclosure having a rigid wall and a deformable wall that define an internal volume. The device further includes at least one pressure measuring element capable of measuring the pressure prevailing in the internal volume. The hydraulic torque measuring device allows a service state in which the internal volume is filled exclusively with an incompressible liquid, and in which the deformable wall is configured to be subjected to a pressure force. In some embodiments, the hydraulic torque measurement device is suitable for use with a gearbox.

Abstract: The present invention relates to a passenger seat (10), in particular for an aircraft cabin, comprising: —a headrest (11), —a backrest (12), —a seat member (13) and—at least one loudspeaker (18) for broadcasting a sound signal to a passenger, —the passenger seat (10) further comprising: —at least one detection means (20) for detecting the presence of the passenger or a part of the passenger's body, and—a control unit (24) configured to selectively command the activation or deactivation of the loudspeaker (18) and/or the modification of a characteristic of a sound signal broadcast by the loudspeaker (18) in accordance with at least one information item from: —an information item relating to the presence of the passenger or a part of the passenger's body determined using the detection means (20), or—an information item concerning the state of the aircraft cabin or aircraft.

Abstract: A method for manufacturing a composite material part having a cellular structure that includes at least one cell delimited by walls. The method includes supplying at least a first core, providing a web of a first fibrous reinforcement comprising a plurality of long discontinuous fibers randomly distributed in a plane, and producing at least one strip of the first fibrous reinforcement. The method further includes producing a second fibrous reinforcement in the shape of a sock, inserting the first core into the sock, draping the strip around the sock containing the first core, placing the sock containing the first core and the wrapped strip in a mold, and thermocompression.

Abstract: A thrust reverser device for an aircraft turbojet engine nacelle an electro-hydrostatic actuation system that includes a motor pump and a first actuation assembly. The first actuation assembly includes a series of at least two actuators configured to be attached to a movable cover of the thrust reverser and to move the movable cover or covers between a retracted position and a deployed position relative to the nacelle. The first electro-hydraulic actuation system further includes a volumetric flow divider with an inlet connected to the motor pump and at least two outlets, wherein each outlet is connected to an actuator. The volumetric flow divider is configured to receive a fluid and to supply the fluid to the actuators with an equal flow rate.

Abstract: An acoustic treatment panel including acoustic absorption cells each comprising a bottom wall, a porous inlet wall, an enclosure extending in an axial direction between the bottom wall and the inlet wall, and a first acoustic horn extending inside the enclosure between a first opening and a second opening that is smaller than said first opening, the first opening facing said inlet wall. Each cell comprises a second horn extending inside the enclosure in the first axial direction between a first opening of the second horn and a second opening of the second horn that is smaller than said first opening.

Abstract: A method of fabricating a part by selectively melting powder is provided. The method includes: depositing a first layer of a first powder having a first element as its main element; depositing, on the first layer, a second layer of a second powder having a second element as its main element, which second element is different from the first element; and moving a first energy beam over the second layer, the energy delivered by the first beam serving to initiate an exothermic reaction between the first element and the second element, the energy given off by the exothermic reaction acting to locally melt together the first and second layers.

Abstract: The method for manufacturing a blade (32) of a turbomachine (100) comprises: —manufacturing a part (4) comprising an air flow path zone (10) and a layer (20) covering the zone, the layer having cavities (21) forming a periodic pattern, the manufacture taking place by injecting a mixture comprising a binder and a power; —removing a larger part of the binder from the part; —sintering the part, and —removing the layer (20) from the part to obtain the blade (32).

Abstract: An electrical system for an aircraft includes first and second buses, first and second electric generators, and first and second AC-to-DC converters. The first bus is connected to an AC network. The second bus is connected to a DC network of the aircraft. The first electric generator is connected to the first bus and a first rotary spool of an engine of the aircraft to exchange mechanical and/or electrical power. The first AC-to-DC converter is connected to the first and second buses. The second electric generator is connected to a second rotary spool of the engine of the aircraft. The second AC-to-DC converter connected to the second electric generator and to the second bus. One or more of the converters operates in a forced mode providing regulation of the electrical power of one or more buses, and/or a free mode providing regulation of a voltage of the second bus.

Abstract: The invention relates to a double-disconnect double-pole bidirectional contactor configured to be mounted on two parallel busbars, comprising, for each pole, an interrupter chamber, in which the following are disposed: a moving bridge having first and second moving contacts; a first fixed contact and a second fixed contact; a pair of magnets, able to generate a magnetic field with a constant direction, so as to generate a magnetic force for moving an arc appearing between the fixed contacts and the moving contacts of the moving bridge passing from a closed state to an open state; four blocks of fins; four arc guides. The two interrupter chambers are configured to simultaneously extinguish arcs having a first current direction for one pole, and arcs having a second current direction for the other pole, the first and second current directions being opposed.

Abstract: A fluid pump for an aircraft turbomachine includes a ring through which a duct passes along a central axis, a rotor driven in rotation with respect to the ring along a main axis offset relative to the central axis. Cavities between the ring and the rotor have volumes that vary according to the angular position of the rotor with respect to the ring. The pump further includes an inlet space for admitting the fluid into the cavities and a discharge space for discharging the fluid from the cavities, the pressure in the discharge space being higher than the pressure in the inlet space. A groove pressurizes the cavities in the discharge space when the rotor rotates.