Abstract: An articulating arm assembly for a passenger seat includes a static portion attachable to the passenger seat, a rotation portion attached to the static portion such that the rotation portion is pivotable about a rotation axis, an arm body attached to the rotation portion, such that the rotation portion and the arm body are movable between a stowed position and a deployed position, and a wiring portion disposed inside the arm body and extending from the arm body into the rotation portion. The wiring portion extends parallel to the rotation axis from the rotation portion toward and into the static portion.

Abstract: An acoustic attenuation panel for a propulsion assembly includes an acoustic front skin having perforations, and a central structure formed from partitions arranged perpendicularly in order to make up cells, wherein the front skin and the central structure form the panel which is made as a single piece and is provided for directly covering a surface of an element of the propulsion assembly forming a rear skin which closes the cells of the central structure at the rear.

Abstract: An electrical supply holding circuit includes a primary stage and a secondary stage. The primary stage includes a voltage connector connected to a supply network, and a primary winding connected to a voltage converter. The secondary stage includes a secondary winding facing the primary winding, the primary and secondary windings forming two coupled inductances, and a voltage controller to which the secondary winding is connected, the voltage controller being connected to a load and controlling a voltage across the terminals of the load. Directions of the currents flowing through the primary and secondary windings are the reverse of one another, and the voltage converter stops the supply to the primary winding when the supply voltage is less than a threshold voltage and resumes the supply to the primary winding when the supply voltage is greater than a threshold voltage.

Abstract: A discharge grille of an intermediate casing of a turbomachine includes a peripheral edge and a seal mounted on the peripheral edge via an attachment system, the seal ensuring the sealing between a first turbomachine member and a second member of the turbomachine, and surrounding the discharge grille of the intermediate casing, the seal having a U-shaped cross section and includes a base plate configured to bear against the first member, a sealing lip configured to bear against the second member through deformation of the sealing lip to ensure air tightness and fire proofing through contact.

Abstract: The present invention relates to a force application device for a control stick of an aircraft comprising a shaft and a control lever configured to rotate the shaft about a first axis, the device comprising: a magnetic brake comprising a braking part configured to be connected to the shaft, and a volume containing a rheological fluid in contact with the braking part, of variable shear resistance as a function of a magnetic field applied to the rheological fluid, a force feedback motor configured to exert a resistive force opposing the rotation of the shaft about the first axis, a motor power source, a movable magnetic element biased towards a position close to the magnetic brake, and distancing means configured to maintain the movable magnetic element in a position away from the magnetic brake, when such distancing means are powered by the power source.

Abstract: An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

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: Turbine shroud assembly comprising sections (10) made from CMC and forming a shroud (1) and a support structure (3), each section having a base (12) with a radially internal face (12a) and a radially external face (12b), from which there extend in a projecting manner an upstream attachment lug (14) and a downstream attachment lug (16), the support structure comprising a collar (31), from which there radially extend in a projecting manner towards the shroud an upstream radial flange (32) and a downstream radial flange (36), by which the lugs of each section of the shroud are retained, the shroud (1) being retained by axial pins (119, 120) which cooperate, on the one hand, with the upstream radial flange, via first and second annular end plates (33, 34), and directly with the downstream radial flange and, on the other hand, with the upstream and downstream attachment lugs, respectively.

Abstract: The invention relates to a fibrous texture intended to form the fibrous reinforcement of a turbine engine blade made of composite material, the texture being in a single piece and having a three-dimensional weave between a plurality of first fiber warp yarns or strands extending in a radial direction and a plurality of first fiber weft yarns or strands extending in a chord direction, the texture comprising a blade root portion and a blade airfoil portion extending between the blade root portion and a free end of the fibrous texture. The blade airfoil portion has a reinforced area in the vicinity of the free end of the texture comprising weft yarns or strands made of second fibers different from the first fibers.

Abstract: A rotating electric machine includes a rotor and a wound stator. The wound stator has a stator shaft, wherein the stator coils are inserted in the rotor, and the stator shaft is inserted in the center of the rotor. At least one angular position sensor of the rotor is inserted in the center of the space delimited by the stator shaft and the rotor.

Abstract: A passenger seat includes a spreader with one or more open slot. The slot may be positioned on a lateral side of the spreader and may receive a portion of a seat base of the passenger seat within the slot. In some aspects, the slot may be elongated, and an insertion opening for the slot is provided in a top side of the spreader.

Abstract: A device for sealing a space at a juncture between elements of a nacelle, the device being non-flammable by heat, having a predetermined shape, and having a proximal end configured to be inserted into the space to be sealed so as to seal it, and a distal end configured to be fastened to an element of the nacelle at a fire area.

Abstract: An aircraft turbojet engine nacelle includes a rear section without a lower bifurcation, the rear section including a thrust reverser system, and the thrust reverser system including a movable cowl. The nacelle includes a guide system including a movable portion and a fixed portion, the movable portion being secured in translation to the movable cowl and cooperating with the fixed portion and the fixed portion being fixed relative to the nacelle. The guide system is disposed proximate to a position called the “6 O'clock” position. In one form, the length of the fixed portion of the guide system is larger than or equal to 50% of the length of the movable portion.

Abstract: A privacy panel assembly for a passenger seat includes a vertically extending panel attached to a lateral surface of the passenger seat such that the vertically extending panel includes a forward edge and an aft edge and at least one sliding mechanism attached to an interior surface of the vertically extending panel. The vertically extending panel includes a stowed configuration and a deployed configuration. In the stowed configuration, the aft edge of the vertically extending panel is disposed on an aft side of a rear surface of a seatback of the passenger seat. In the deployed configuration, the aft edge of the vertically extending panel is approximately aligned with a seating surface of the seatback on a forward side of the passenger seat.

Abstract: A hinge assembly for an aircraft overhead storage bin that includes a housing having a hinge space and a hinge opening defined therein, an arm pivotably connected to the housing within the hinge space, and a dampener. The hinge opening communicates the hinge space with an exterior of the housing. The arm is pivotable between a closed position and an open position and extends through the hinge opening such that the first end of the arm is positioned outside of the housing. The dampener includes first and second ends. The first end is connected to the housing and the second end is connected to the arm. The dampener biases the arm from the closed position to the open position.

Abstract: A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

Abstract: The invention relates to a method for controlling a turbomachine comprising a gas generator, the turbomachine comprising an electric machine forming a device for injecting torque into/removing torque from one of the low pressure/high pressure rotation shafts of said gas generator. Said method comprises a step of implementing a fuel control loop in order to determine a fuel flow setpoint into the combustion chamber, and comprising, in the event that at least one operability limit is reached, determining a corrected fuel flow setpoint, said corrected fuel flow setpoint exhibiting a difference in relation to the setpoint. Said method also comprises a step of implementing a torque control loop in order to determine a torque setpoint for the electric machine, and comprising determining a torque correction quantity as a function of said difference, said torque setpoint being determined as a function of said torque correction quantity.

Abstract: A method for manufacturing a part of nitrided steel includes a step of nitriding the part. After nitriding, laser shocking is carried out on a surface of the nitrided part.

Abstract: A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

Abstract: A turbofan engine has a primary duct , in which there flows a primary flow at a primary pressure and a secondary duct, which radially surrounds the primary duct and in which there flows a secondary flow at a secondary pressure. The primary duct includes at least one compressor configured to compress the primary flow , a turbine driving the compressor in rotation and a combustion chamber designed to receive, at an inlet, the primary air flow compressed by the compressor The turbomachine further includes a cooling circuit extending between the compressor and the turbine.The cooling circuit has an air flow rate regulating device arranged upstream of the turbine and having at least one valve that is configured to move between an open position and a closed position, located between the compressor and the combustion chamber in the primary duct and the pressure (PS) in the secondary duct.