Abstract: A quenching chamber includes, for each zone of contact between a mobile contact and two fixed contacts, respectively, two pairs of guides that extend from the mobile contact and the contact zone in question, respectively, so as to guide, under the action of a magnetic field of constant direction, an electric arc. The pairs of guides follow one after the other in the direction of the magnetic field, and each pair of guides delineates between them a guiding zone. The guiding zones overlap at least partially in the direction of the magnetic field.

Abstract: The invention relates to a method for locating a target by means of a detecting device comprising a photodetector comprising N×M quadrants positioned with respect to a sighting axis of the detecting device, the photodetector being configured to detect optical signals from the target to be detected, said method being implemented in a processing unit of said device and comprising the following steps, the target scattering an optical signal: —acquiring the signals detected by each quadrant, which correspond to the signals scattered by the target toward the quadrants; —processing the acquired signals to determine an elevation angle error and an azimuth angle error of the direction of the target with respect to the sighting axis of the device; —processing the acquired signals with a view to deducing therefrom indicators of the distribution of the signals detected by the quadrants; —processing the determined elevation angle error and azimuth angle error with a view to deducing therefrom indicators of the theoretica

Abstract: A method for marking the surface of an aluminum or aluminum alloy part includes an anodizing step, a sealing step, and a marking step that uses a fiber laser beam. The marking method may be used for the manufacture or marking of aluminum or aluminum alloy parts intended for the aeronautical, aerospace, automotive, railway, watchmaking, medical, nuclear and oil industries.

Abstract: A method for drying a blank of a part made of a carbon/carbon composite material impregnated with a sol-gel solution, the solution including a solvent and one or more compounds, in a system forming an oven includes gelling the solution so as to form a gel within the blank disposed in the chamber by heating a chamber, where a gas circulator and a desaturation component are deactivated, so as to restrict circulation and desaturation of the gas in a solvent, and drying the gel within the blank by heating, where the gas circulator and the desaturation component are activated, so as to enable circulation and desaturation of the gas in a solvent.

Abstract: A device for connection to an on-board multiplexed network of communication by multi-mode optical fibers for an aircraft, the device comprising a first optical component for modifying the spatial profile of a light beam, comprising a multi-mode optical input terminal configured to be connected to a first multi-mode optical fiber and single-mode optical output terminals, and a second optical component for modifying the spatial profile of a light beam, comprising single-mode optical input terminals and a multi-mode optical output terminal configured to be connected to a second multi-mode optical fiber. It further comprises an optical harness for switching and reassigning a transmission channel including single-mode optical inputs coupled to the single-mode optical output terminals of the first component, single-mode optical outputs coupled to the single-mode optical input terminals of the second optical component, and single-mode waveguides.

Abstract: A turbomachine includes an enclosure lubrication and pressurization assembly having at least one lubricated enclosure protected by two seals. The turbomachine further includes a primary flow path surrounding the at least one lubricated enclosure, and in which circulates a primary flow passing through at least one compressor of the turbomachine. The assembly further includes an electric compressor supplied with air and connected to the at least one lubricated enclosure in order to introduce air under pressure into the enclosure through the seals.

Abstract: A device for attaching a connecting rod small end for a thrust reversal cascade flap onto a fixed internal structure of a turbojet engine nacelle includes a fitting configured to be fixed to the internal structure and a connection interface forming a joint between the connecting rod small end and the fitting. The device further includes a removable fork configured to cooperate with the connection interface, wherein the fork and the connection interface are arranged inside the fitting.

Abstract: The present application relates to an assembly for a turbine engine (1), comprising a first rotor (2) which is rotatable about a longitudinal axis (X-X) of the turbine engine (1), the first rotor (2) comprising a first arm (26); a second rotor (3) which is rotatable about the longitudinal axis (X-X) and comprises a second arm (36); a first sealing ring (4) which is centred on the longitudinal axis (X-X), is arranged radially outside the first arm (26) and comprises a first radial flange (40) fixedly mounted between the first arm (26) and the second arm (36); and a second sealing ring (5) which is separate from the first sealing ring (4), is centred on the longitudinal axis (X-X) and is arranged radially outside the second arm (36), the second sealing ring (5) comprising a first part (51) which is designed to come into contact with the second rotor (3), and a second part (52) which is separate from the first part (51) and is designed to come into contact with the first sealing ring (4).

Abstract: A method for navigating a carrier using a Kalman filter estimating a navigation state of a carrier, comprising: obtaining, from a signal transmitted by the satellite and subsequently received by the carrier, a delta range measured between the carrier and a satellite and another measured kinematic datum which is associated with the satellite, generating, from position data for the carrier and the satellite in the navigation state, an estimated delta range between the carrier and the satellite, calculating, using the delta ranges, a delta range innovation associated with the satellite, carrying out a test on the delta range innovation, the test result indicating whether or not the signal was a multi-path signal, using, by means of the filter, the kinematic datum as an observation to update the navigation state provided that the test result indicates that the signal was not a multi-path signal.

Abstract: A method for manufacturing at least one portion of a part using successive deposition of layers, involving the steps of: a) depositing a first layer of a molten metal on a substrate such that a first metal strip is formed on the substrate; b) depositing a second layer of a molten metal on the first strip such that a second metal strip is formed on the first strip; and c) repeating steps a) and then b) for each new metal layer to be deposited on a preceding strip until the at least one portion of the part has been formed. The method may further include step d) compressing the formed bead after performing n instances of step c), n being greater than or equal to 1. The step of compressing the formed bead may be performed before the complete cooling of said bead.

Abstract: Described is a passenger seat having a seat bottom, a seat back, and a privacy divider. The seat back may have a stationary portion and a moveable portion, wherein the moveable portion is substantially upright in stowed position and is substantially horizontal over the seat bottom in a deployed position. The privacy divider may be coupled to at least an upper surface of the moveable portion in the deployed position.

Abstract: A landing gear system includes a landing gear assembly coupled to a body of a vehicle and configured for reciprocating motion between a retracted position and an extended position. A fail-secure uplock assembly is reciprocal between a locked state and an unlocked state. A first electromagnet and a first permanent magnet are mounted to the body, and a second electromagnet and a second permanent magnet are mounted to a component of the landing gear assembly. The first and second electromagnets generate magnetic fields with reversible polarities. When the landing gear assembly is in the retracted position, the first permanent magnet is attracted to the second permanent magnet. The first electromagnet is attracted to the second electromagnet when the uplock assembly is in the locked state and is repelled by the second electromagnet when the uplock assembly is in the unlocked state.

Abstract: A rolling bearing assembly includes an inner ring and an outer ring that are coaxial about an axis of rotation and between which rolling elements are arranged. An annular metal rolling bearing cage is centered about the axis of rotation and arranged radially between the inner ring and the outer ring, the annular cage having recesses for retaining rolling elements, an outer annular face facing the outer ring, and an inner annular face facing the inner ring. At least one insert at least one tubular portion engaged in a recess of the annular cage, a tubular portion of the insert being connected at one radial end to a rim arranged in abutment against the inner annular face or the outer annular face of the annular cage. A latching means on the insert cooperates with a latching means in the annular cage to hold the insert in a recess.

Abstract: A landing gear system for a vehicle includes a landing gear configured for reciprocating motion between a stowed position and a deployed position. The landing gear has a linkage with a first link rotatably coupled to a second link. The linkage reciprocates between folded and extended states when the landing gear reciprocates between the stowed and deployed positions, respectively. A fail-secure downlock includes first and second electromagnets fixedly positioned relative to the first and second links, respectively. The first electromagnet is proximate to the second electromagnet when the landing gear is in the stowed position. The first electromagnet is attracted to the second electromagnet when the downlock is in the locked state. The first electromagnet is repelled by the second electromagnet when the downlock is in the unlocked state.

Abstract: The invention relates to a blade comprising a shield (14) attached to the upstream end of the body of the blade, the shield (14) comprising an upstream end forming a leading edge of the blade, the shield (14) further comprising a nose (141) upstream from which the leading edge is located, an pressure-face fin and an suction-face fin laterally attached on the blade, the fins extending from the nose, the blade comprising a defrosting air passage duct (15) arranged inside the nose and extending radially inside the nose, the duct (15) having an inner end (151) emerging opposite the root (125) and a radially external end emerging from the nose between the leading edge and its junction at the pressure-face fin.

Abstract: A method of consolidation includes placing a fibrous preform in the shaping recess of a shaping tool, and supplying the shaping tool with a gas phase to obtain a deposit in the fibrous preform, the shaping tool for the vapor phase chemical infiltration including first and second portions, having respectively first and second shaping zones surrounded by a first and second edge zones, the first and the second shaping zone defining a shaping recess to receive the fibrous preform. A gas injection port is present at least partially in the first or second edge zone and a gas outlet port is present at least partially in the first or second edge zone, the gas injection port and the gas outlet port placing the shaping recess in fluid communication with the outside of the shaping tool. Outer faces of the first and second portion are impermeable to gas.

Abstract: Described is a seat track stud for attaching a passenger seat to a seat track having a first stud member, a second stud member, and a pin. The first stud member includes a base portion with at least one flanged edge, a first securing portion extending from the base portion and defining a first securing portion opening; and a second securing portion extending from the base portion at a location opposite the first securing portion and defining a second securing portion opening. The second stud member includes a connecting portion that defines a connecting portion opening and that is sized to fit between the first securing portion and the second securing portion. The pin extends through the first securing portion opening, the connecting portion opening, and the second securing portion opening.

Abstract: A structural shroud for a passenger seat assembly includes a hollow body having a first end, a second end opposite from the first end, and a central cavity between the first end and the second end. In certain embodiments, the structural shroud may include a magnesium alloy and/or an aluminum alloy, and may be formed via casting, forging, and/or additive manufacturing, among others. In some embodiments, a base frame assembly for a passenger seat assembly includes a monolithic base frame having a first leg portion and a first tube portion integrally formed with the first leg portion.

Abstract: An aircraft landing gear having a male part interlocked with a female part along an interlocking direction is provided. The external contact surface of the male part, when it is observed along the interlocking direction, can be an exclusively convex closed surface having external contact surface portions in the form of rounded lobes that form obstacles to the pivoting of the female part with respect to the male part about the interlocking direction. The aircraft landing gear is suitable for use with an aircraft.

Abstract: Turbomachine including: a fan arranged along a longitudinal axis of the turbomachine, a primary duct able to channel a primary air flow from the fan through a compressor, a combustion chamber and a turbine of the turbomachine, an annular nacelle surrounding the fan so as to delimit a secondary duct able to channel a secondary air flow from the fan the temperature of which is less than that of the primary air flow of the fan, the secondary air flow extending around the primary air flow of the fan and, engine support arms arranged around the longitudinal axis between the annular nacelle and a hub which delimits the primary and secondary ducts characterized in that it also includes an electrical energy generation device mounted facing or so as to be able to be arranged facing one of the support arms.