Abstract: The system for controlling the speed of movement of a sliding door for an aircraft comprises a means for electromagnetically braking the door including a transmission shaft and electromagnetic resistive means. The resistive means are autonomous and include a control law relating a first damping value to a first speed threshold of the speed of movement of the door, a second damping value to a second speed threshold of the speed of movement of the door, the resistive means applying on the transmission shaft the resistive torque equal to a first torque proportional to the first damping value when the speed of movement is higher than the first speed threshold, and applying the resistive torque equal to the sum of the first torque and of a second torque proportional to the second damping value when the speed of movement is higher than the second speed threshold.

Abstract: Rotor of a rotary electric machine, comprising a body having two opposite lateral surfaces and a surface of revolution, two short-circuiting rings disposed in contact with each lateral surface of the body, and conductors disposed in slots formed on the surface of revolution of the body and each connected to the short-circuiting rings, characterised in that each conductor comprises at least one shoulder aligned with a lateral surface of the body.

Abstract: An assembly includes an inner wall delimiting a cavity, the inner wall having a first surface facing the cavity, and a second surface opposite the first surface with respect to the cavity, and a sealing device attached to the second surface and including a sealing layer including a material expandable when an opening is formed in the inner wall, and a guide attached to the sealing layer so as to exert a stress on the sealing layer to control a direction of expansion of the material of the sealing layer. The sealing layer has a first face and a second face, and the guide includes a first film attached to the first face and a second film attached to the second face.

Abstract: A power contactor including: a fixed part; a movable part able to come into contact with the fixed part and to move between an open position and a closed position of the contactor, the movable part including at least one power contact; an auxiliary contact and a pyrotechnic actuator, the auxiliary contact and the pyrotechnic actuator being placed in parallel with the power contact, and the pyrotechnic actuator being configured to be triggered during a levitation of the contactor in such a way as to move the contactor into the open position; and a motor configured to actuate the movable part and to put it in contact with the fixed part characterized in that the power contact and the auxiliary contact are desynchronized in such a way that when the contactor is closed, the power contact comes into contact with the fixed part before the auxiliary contact

Abstract: A method for producing a part, in particular a part made of composite material, in particular for a turbomachine, including at least: a step of producing a preform, during which a fibrous preform intended to form an outer skin of the part is produced; a step of producing a core, during which a rigid core, in particular a hollow rigid core, intended to form a framework of the part is produced; an insertion step, during which the rigid core is inserted into the fibrous preform, an injection step, during which a matrix is injected into the fibrous preform; and a heat-treatment step, during which polymerisation of the matrix is carried out.

Abstract: An adapter is configured to be disposed on the inlet of an oil tank of an aircraft engine. The adapter includes a plug between the adapter and the exterior, and a flapper between the adapter and the oil tank. An adapter cavity located between them is set to negative pressure during flights. When the aircraft is back on the ground, this negative pressure has to be counteracted to open the plug, which can make the opening operation difficult. The adapter includes a lever that counteracts the negative pressure in the cavity of the adapter to allow easy opening of the plug with limited force.

Abstract: An annular air intake lip for a nacelle of an aircraft propulsion assembly is provided. The annular lip can extend about an axis of revolution and include: an external annular wall, an internal annular wall, an upstream annular wall connecting the external and internal annular walls to define an annular cavity therebetween. At least part of the annular lip can include at least one heat transfer coating that is made from a carbon allotrope material.

Abstract: This parachute comprising a canopy having a leading edge and a trailing edge opposite the leading edge, suspension lines each having a first end attached to the leading edge and a second end that is designed to bear a load, and a slider having through-elements for the suspension lines to pass through, said elements being connected to one another by attachment means, each of said through-elements being passed through by one of the suspension lines and being free to move in translation relative thereto, the slider being designed to slide along the suspension lines that pass through the through-elements in the direction from the first ends of said suspension lines towards their second ends under the effect of gravity and the force generated by the suspension lines spreading apart when the parachute starts a descent, tightening and spreading apart the suspension lines as the canopy inflates.

Abstract: A power contactor including: a fixed part including two fixed elements; a moveable part able to come into contact with the fixed part and to move between an open position and closed position of the contactor, the moveable part including two switching elements and two conducting elements, and the distance between the fixed part and the two conducting elements being greater than the distance between the fixed part and the two switching elements in open position of the contactor, such that the switching elements come into contact with the fixed part before the conducting elements when the contactor changes from open position to closed position; and a motor configured to actuate and place the moveable part in contact with the fixed part.

Abstract: An air inlet of an aircraft propulsion unit comprising thrust reversal means configured to modify a bypass air flow circulating from upstream to downstream in a bypass duct into a reverse air flow circulating from downstream to upstream. The air inlet comprising an interior wall defining openings and, in each opening, a mobile member that comprises a covering wall and a deflecting wall and is mounted so as to pivot between a covering position, in which the covering wall obstructs the opening so as to guide the bypass air flow and promote a thrust phase, and a deflecting position, in which the deflecting wall obstructs the opening so as to separate the reverse air flow and promote a thrust reversal phase.

Abstract: The present disclosure relates to a system for supplying fuel to a turbomachine. In some embodiments, a fuel circuit includes a pressurisation valve at an outlet of the system and a pump. The circuit may include a flow rate sensor arranged between the outlet of the pump and the pressurisation valve. In some embodiments, the flow rate sensor may include a sliding drawer, a restoring spring, and a sensor for detecting the position of said drawer in order to indicate the flow passing through the flow rate sensor. The system may include a device arranged to drive the pump with a controllable rotational speed and a control configured to control the device on the basis of a measurement supplied by the flow rate sensor, in such a way as to adapt the rotational speed of the pump shaft.

Abstract: A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots.

Abstract: A system for controlling the activation/deactivation of an electromagnetic shielding screen of a porthole or a protective window of an optoelectronic equipment, which includes, a radiofrequency electromagnetic sensor, with a bandwidth adapted to a cut-off band of said shielding screen corresponding to a range of electromagnetic fields to be blocked, connected to a detector-rectifier with a sensitivity higher than a minimum value of the power of an electromagnetic field to be blocked by means of said shielding screen and a device for activating/deactivating said electromagnetic shielding screen, said detector-rectifier being configured, in the presence of the electromagnetic field with a power exceeding said minimum value, to activate said device for activating/deactivating the electromagnetic shielding screen by capturing the electromagnetic energy supplied by said electromagnetic fields with a power exceeding said minimum value.

Abstract: The invention relates to a method for estimating the direction of arrival of an electromagnetic wave at an antenna array (2), comprising the steps of: —estimating (202) a covariance matrix of signals acquired by the antenna array (2); —calculating (204) a normalised eigenvector of the covariance matrix; —correlating (205) the normalised eigenvector with a first reference table and a second reference table so as to produce a first correlation spectrum and a second correlation spectrum comprising correlation indices associated, respectively, with different directions of arrival; —constructing (312) a third reference table by linear combination of the first reference table and the second reference table with a polarisation component of the electromagnetic wave in the first direction and the second direction, respectively; —correlating (314) the normalised eigenvector with the third reference table so as to produce a third correlation spectrum comprising correlation indices associated with different directions of

Abstract: An electronic device for diagnosing the condition of a system of actuators of an aircraft turbine engine, the device being configured to be coupled to an electrical wiring harness of a turbine engine connecting a computer of a turbine engine to a system of actuators of the turbine engine, the device including a power supply block to power the device, a connection block configured to enable the connection of the device to the electrical wiring harness of the turbine engine to be diagnosed, a communication block configured to send information to a user and to receive instructions from the user, and a control block including a test signal transmission module and modules for measuring the signals received by the device in response to the test signals over a work cycle of the system of actuators of the turbine engine.

Abstract: An aircraft turbomachine has a gas generator that includes, along a longitudinal axis (X), at least one compressor, a combustion chamber, and at least one turbine. The turbomachine further includes at least one duct for supplying liquid to at least one member chosen from an oil jet and a fuel injector. The duct (20) has rectilinear portions and bent portions and includes at least one region in which the liquid is liable to coke. The turbomachine also includes at least one turbulence element in the at least one region in the duct.

Abstract: A fan module for an aircraft turbine engine includes a fan having variable pitch blades and an oil transfer device configured to provide a transfer of oil between a stator and a rotor. The oil transfer device includes a stator ring having internal oil ducts, a shaft inserted into the ring and having internal oil ducts, and an annular support of the ring configured to deform elastically to allow movements of the ring in the radial direction. A plain bearing is located between the ring and the shaft, and roller bearings are mounted between the ring and the shaft on either side of the plain bearing.

Abstract: A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.

Abstract: Described is an adjustable friction slider assembly having a rail member and a carriage assembly moveably coupled to the rail member, the carriage assembly having a bracket member and a plurality of roller elements moveably coupled to the rail member and coupled to the bracket member using a plurality of attachment members, the plurality of roller elements comprising at least one adjustable roller element coupled to the bracket member using a moveable attachment member, wherein moving the moveable attachment member adjusts a friction between the plurality of roller elements and the rail member.

Abstract: A method for repairing an end plate of a turbomachine rotor, the end plate including a crown having at least two collar fastening holes and at least one balancing-weight fastening hole located between the two collar fastening holes, each collar fastening hole being equipped with a crimped nut, the crown having a damaged portion between two collar fastening holes, the method including the steps of removing the two crimped nuts located on either side of the damage; removing the damaged crown portion, for example by machining; putting in place a strip in the form of a crown portion closing off the removed crown portion, the strip having at least one balancing-weight fastening hole and two mounting holes; fastening the strip to the crown with two crimped nuts, which penetrate the mounting holes, by crimping each nut in a collar fastening hole.