Abstract: The invention relates to an assembly for rotationally friction driving the wheel of an airplane (3) provided with a driving track (4) and so mounted as to rotate about an axis of rotation on an axle (2) carried by the lower part of an airplane landing gear, with the assembly comprising: a base (22) intended to be fixed to the lower part of the landing gear; two arms (24) mounted to pivot on the base; rollers (21) so mounted as to rotate at the end of each arm, with each roller being associated with a pinion for rotationally driving (31) the roller; a central pinion (26) so mounted as to rotate along the arms pivot axis so that the rollers driving pinions engage with the central pinion; actuating means (29) so acting on the arms of the assembly as to position same either in a disengaged position in which the rollers are separated from the driving track, or in an engaged position in which the rollers are held to rest on the driving track with a predetermined bearing force.

Abstract: A titanium alloy having at least 4% by weight aluminum and at least 0.1% by weight oxygen, the alloy also including at least one element selected from vanadium, molybdenum, chromium, and iron. The titanium alloy also includes hafnium in a proportion by weight of at least 0.1%.

Abstract: The invention relates to a method for managing the braking of an aircraft fitted with undercarriages (1) bearing braked wheels (2), the method comprising the step of generating braking commands by means of a braking computer (4) for each of the braked wheels as a function of longitudinal speed information representative of a longitudinal movement of the wheels in question, characterized in that there is placed at the bottom of the undercarriage, close to the braked wheels, a sensor adapted for generating a signal that can be used for generating the longitudinal speed information used for generating the braking commands.

Abstract: An aircraft landing gear including an axle and a wheel (5) that includes a rim (6) mounted to turn on the axle about a first rotation axis (X1), the landing gear further comprising an actuator (12) for driving the wheel (5) in rotation. The rim (6) includes obstacles (33) that project from a lateral face (F) of the rim and the driving actuator includes a lead screw (32) mounted to turn about a second rotation axis (X2) perpendicular to the first rotation axis (X1) and adapted to cooperate with the obstacles of the rim to drive the wheel in rotation.

Abstract: The invention relates to a brake actuator for an aircraft hydraulic brake, which is intended to be added into one of the cavities of a brake ring, the actuator comprising: a liner (1) designed to be housed sealingly in the cavity of the ring; a piston (3) mounted to slide sealingly in the liner along an axis of sliding so as to apply a braking force when a fluid is introduced under pressure into the cavity; a wear compensation device (10) which defines a position to which the piston retreats into the liner by means of a mobile stop (11; 111) that can be moved forward by the piston as a braking force is applied; an elastic return member (18) returning the piston towards the retracted position bearing against the mobile stop; according to the invention, the mobile stop is associated with a notched indexing member (13) allowing the mobile stop to move under the thrust of the piston, but preventing any return motion of the mobile stop with respect to the liner.

Abstract: A method of fabricating an element (25) out of composite material, the element comprising three arms (22, 23, 24) arranged in a triangle. The method comprises the operations of: fabricating a three-dimensionally woven preform from reinforcing fibers and including through slots defining two arms (22, 23) and two half-arms that are all parallel and contiguous in pairs, each arm (22, 23) having one end whereby it is connected to a half-arm and another end whereby it is connected to the other arm (22, 23); shaping the preform by deploying it and by uniting its two half-arms in order to give it a triangle configuration; securing together the half-arms by stitching with reinforcing fibers; and injecting resin into the preform and polymerizing the resin.

Abstract: Supporting tool (1) for supporting a substantially cylindrical part, like a landing gear rod or cylinder, said supporting tool comprising a metallic frame carrying at least one metallic ring (3) in electrical conductive relation with the frame, wherein the metallic ring carries a plurality of conical spikes (6) of non-conductive material projecting inward so as to engage the part with limited contact surface when said part is in place within the tool, said ring being openable so as to allow the part to be inserted into the ring and closable after the part has been inserted.

Abstract: The invention relates to a brake actuator for an aircraft hydraulic brake, which is intended to be added into one of the cavities of a brake ring, the actuator comprising a liner (1) designed to be housed sealingly in the cavity of the ring, a piston (3) mounted to slide sealingly in the liner along an axis of sliding (X) so as to apply a braking force on friction pads when a fluid is introduced under pressure into the cavity, and having a determined operational travel, a wear compensation device (10) which defines a position to which the piston retreats into the liner by means of a mobile stop (11) that can be moved forward by the piston as a braking force is applied, and an elastic return member (16) returning the piston towards the retracted position bearing against the mobile stop.

Abstract: A method for the reconditioning and use of brake discs of the rear stator type with studs. The method includes the steps of using a first disc (12) during a first life, using a second disc (112) during a first life, after the first life of the first disc and the first life of the second disc, machining a friction surface on one of the discs and a rear surface on the other of the discs so that one of the surfaces has at least one shoulder (17) and the other of the surfaces has at least one notch (118). Finally, the first disc is nested in the second disc such that the notch and the shoulder cooperate so as to center the discs.

Abstract: The invention relates to a method for fixing to an aircraft landing gear (1) at least one actuator (30) for rotatably driving a wheel (3) which is rotatably mounted on an axle (2) of the landing gear, the wheel being associated with a brake (5) which comprises an actuator carrier (8) which carries brake actuators, the actuator carrier being fitted onto the axle and stopped in terms of rotation by an obstacle (12) which is fixedly joined to the landing gear and which is introduced into one of the stop holes (11) of the actuator carrier, wherein the drive actuator is fixedly joined to the actuator carrier in the region of a stop hole of the actuator carrier which does not receive the obstacle.

Abstract: The invention relates to a method of using and renovating a brake disk (9), the method comprising steps of using the disk in a plurality of lives and compensating for a reduction in the thickness of the disk after each life by assembling the disk with a complementary portion or by associating the disk with another disk of rotor or stator type if the disk is itself respectively of stator or rotor type.

Abstract: The invention relates to a device for maneuvering, on the ground, a door of an aircraft landing gear, the door being linked with door maneuvering means and uplock means for locking the door when it reaches the closed position, at least one unlocking electromechanical actuator arranged to act upon the uplock means with a view to deactivating them during opening of the door in flight. According to the invention, the device comprises control means 17 which can be operated by an operator on the ground in order to control at least: an opening sequence during which the unlocking electromechanical actuator is actuated in order to deactivate the uplock means, a closing sequence during which the maneuvering means are actuated in order to close the door again.

Abstract: The invention relates to an aircraft landing gear equipped with a steering device (7) for orienting the wheels (5), the steering device (7) comprising a body (8) in which is incorporated an electromechanical actuator (41) equipped with an electric motor (42). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel (5) to the rest of the landing gear (1) when the aircraft is on the ground. The body (8) of the steering device (7) is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body (8) of the steering device (7) and the strut assembly (2) of the landing gear to damp the vibration between the body (8) of the steering device (7) and the strut assembly (2).

Abstract: A method of coating the surface of a metal substrate includes a) applying a first composition on the surface of a metal substrate, the first composition being a solution comprising a liquid medium including sol-gel precursors of alcoxysilane type or of metallo-organic type; b) subjecting the first composition to first heat treatment to form an anchor layer on the metal substrate in which the sol-gel precursors are bonded to the metal substrate, a first temperature being imposed during the first heat treatment that is sufficient to eliminate all or part of the liquid medium and to encourage the bonding of the sol-gel precursors to the metal substrate; and c) applying a second composition on the anchor layer. The second composition includes coating compounds to obtain a coating on the anchor layer by forming bonds between the sol-gel precursors and the coating compounds.

Abstract: An undercarriage comprising at least: a wheel mounted on an axle (3); a brake comprising a torsion tube (9), friction members (11) mounted around the torsion tube, and at least one brake actuator (13) for selectively exerting a braking force on the friction members; and drive means for driving rotation of the wheel and comprising an electric motor (14) that is connected to a rim (5) of the wheel (4) by a coupler member (15). The coupler member extends at least in part around the axle (3) between the axle and the torsion tube (9) of the brake.

Abstract: A drive device for driving a helical fiber sheet for needling, the device including a needling table having a stationary top surface for receiving a helical fiber sheet for needling, a circular turntable positioned under the top surface of the needling table and having a plurality of drive needles vertically mounted thereon, the drive needles passing through the needling table and projecting relative to its top surface, the drive needles being positioned on at least one diameter of the turntable, and a drive system constructed and arranged to drive the turntable in rotation relative to the top surface of the needling table about a vertical axis.

Abstract: The invention relates to a measurement device for measuring the rotational speed of a vehicle wheel, the measurement device comprising a body (22) incorporating: a rotor (30) which can be rotated by the wheel and on which at least one permanent magnet (33) is mounted; a stator (31) comprising a winding (36) generating a measurement voltage when the wheel (2) and therefore the permanent magnet turn, the measurement voltage being indicative of the rotational speed of the wheel; an electronic board (32) comprising processing means for processing the measurement voltage; power supply means designed to generate, from the measurement voltage, a power supply voltage intended to power the electronic board.

Abstract: An aircraft landing gear comprising an axle (3) intended to receive a wheel (4) comprising a rim (6) mounted to rotate on the axle (3) by means of at least one rolling bearing (8). The rolling bearing (8) comprises an inner ring (11) mounted around the axle (3) and an outer ring (12) rotationally secured to the rim (6) of the wheel (4). The landing gear further comprising a measurement device (21) intended to perform measurements of at least one operating parameter of the landing gear. The measurement device (21) is incorporated in the rolling bearing (8) by being secured to one of the inner or outer rings of the rolling bearing (8).

Abstract: Sensor (1) comprising: a casing (2) delimiting an internal volume (3) and having a passage (31) between this internal volume and a first external zone (Z1) external to the casing; a moving part (4) able to move inside the said internal volume (3); detection means (5) for detecting a movement of the said moving part (4) comprising a detection portion (51) extending in the passage (31), and having a groove (52) open to the outside of the detection portion (51), this groove (52) extending between the said first external zone (Z1) external to the casing and the said internal volume (3) internal to the casing. The sensor (1) comprises first sealing means (14) positioned around the detection portion (51) inside the passage (31), these first sealing means (14) being arranged in such a way as to prevent fluid from passing between the internal volume (3) and the first external zone (Z1) via said groove (52).

Abstract: A device, which connects a gearmotor to an aircraft wheel, comprising: a casing rotatably carrying a shaft driven by the gearmotor, the shaft having a fluted portion on which a gearwheel is mounted to slide along a longitudinal axis of the shaft without rotating relative to the shaft; a toothed ring for constraining to rotate with the aircraft wheel; and structure for moving the gearwheel axially between a retracted position (disengaged from the toothed ring) and an engaged position (gearwheel meshes with the toothed ring). The structure for moving the gearwheel comprises a hollow screw-and-nut assembly extending around the shaft. One element of the assembly is axially secured to the gearwheel but prevented from rotating by an anti-rotation member. The other element of the assembly is rotatably mounted inside the casing to be driven selectively by an electric motor so that rotating the electric motor causes the gearwheel to move axially.