Abstract: Control system (1) comprising a control rod (5) extending between a first zone (2) situated in a hydraulic chamber delimited by a chamber wall (3) and a second zone (4) situated outside the hydraulic chamber. The control system (1) further comprising a seal (6) arranged around and against this control rod (5) to oppose the passage of fluid between the first and second zones (2, 4). The system further comprises a guide piece (7) assembled removably with respect to the chamber wall (3), the seal (6) is assembled inside the guide piece (7) so as to allow relative movement of the rod (5) with respect to the guide piece (7) while at the same time achieving sealing between the first and second zones (2, 4).

Abstract: A sensor (1) comprising: a housing (2) defining an internal volume (3); a movable part (4); detector means (5) for detecting movement of the movable part (4); transfer means (6) passing through a first opening (7) of the housing (2) to control movement of the movable part (4) from a first external zone (8); and first sealing means (9) for opposing the passage of fluid coming from the first external zone (8) towards said internal volume (3). The housing (2) includes a second opening (10) extending between the internal volume (3) and a second external zone (11); and second sealing means (12) between the internal volume (3) and the second external zone (11), the second sealing means being adapted to break so as to allow fluid to pass as soon as a first predetermined pressure difference is exceeded.

Abstract: A honing tool (1) for honing a cylindrical external surface (2) of a rod (3). The tool comprises a plurality of honing inserts (4) adapted to hone a metal; and a support (5) for the honing inserts. The inserts (4) are carried by the support (5) and define a passage (6) around which the inserts (4) are to be found and in which the cylindrical external surface (2) of the rod (3) is insertable. The tool (1) includes a plurality of sliding skids (7) carried by the support (5), the sliding skids (7) and the honing inserts (4) being arranged to be capable of coming simultaneously into contact against the cylindrical external surface (2) of the rod (3) when the rod is placed inside said passage (6) and so as to be able to center the cylindrical external surface (2) inside said passage (6).

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: Drive equipment for rotating by friction an aircraft wheel equipped with a drive track and mounted to turn about an axis (X) on an axle of an aircraft undercarriage. The equipment comprise a base (22), a slide (24) mounted on the base on a sliding axis extending in a radial direction (R1, R1), a support (26) pivotable on the slide on an axis parallel to the rotation axis of the wheel; two rollers (21) rotatable on rotation axes parallel to the pivot axis; a central shaft (28) mounted for rotation on the support and being in engagement with the two rollers to provide their rotation; and an actuator (23A, 23B, 30) for moving the slide and the support between a disengagement position with the rollers distant from the wheel drive track and an engagement position with the rollers are held in contact with the drive track of the wheel.

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: A method of fabricating an aircraft landing gear rocker beam comprising a body having a clevis (24) with two lugs (19, 21) parallel to a direction that is radial relative to the body, the method comprising the steps of: forming a first mandrel; applying one or more first braided fiber layers (11) on the first mandrel; fitting a second mandrel element on the assembly as constituted in this way, the second mandrel element extending between the two lugs (19, 21) of the clevis (24) that is to be formed; applying one or more second braided fiber layers (17) on the assembly as constituted in this way; injecting resin into the various layers (11, 17) and polymerizing the resin; and machining the resulting workpiece blank in order to cut away a region of the second braided layers (17) in order to separate the two lugs (19, 21) of the clevis (24) from each other.

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: 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: 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: 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: 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: 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: A hydraulic shimmy damper that resolves drawbacks in several known shimmy dampers, such as damping characteristics that are dependent on oil temperature variations. The disclosed shimmy damper includes a hydraulic compensator (40) having an internal fluid volume that is significantly more important than a fluid volume expelled from the body of the shimmy damper when its piston moves fore and aft. The shimmy damper also includes a hydraulic manifold (30) arranged between the body and the hydraulic compensator and defining a transfer channel between chambers in the piston that is connected to the hydraulic compensator. The manifold receives interchangeable hydraulic cartridge-type valves (CV1,RV1; CV2,RV2) for metering the fluid flowing from the chambers to the transfer channel, and allows the fluid to freely enter the chambers from the transfer channel. The present shimmy damper is therefore much less sensitive to oil temperature variation under intense shimmy.

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: An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident airflow and wherein in the second configuration the fairing is arranged to deflect debris or spray propelled from one or more of the wheels.

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).