Abstract: The invention relates to an aircraft undercarriage comprising: a strut (1) for connecting to the aircraft, a slide rod (3) slidably engaged in leaktight manner in the strut via the bottom opening, which rod carries at least one wheel at its bottom end, a diaphragm (7) carried by a support (8) attached to the top wall of the strut to co-operate in leaktight manner with an inside wall of the slide rod so as to define a first chamber (C1) under the diaphragm inside the rod and completely filled with hydraulic fluid, and a second chamber (C2) above the diaphragm and partially filled with hydraulic fluid, a throttle needle (10) secured to the slide rod and penetrating into a calibrated orifice (12) in the diaphragm so as to define a calibrated fluid passage between the first and second chambers, and angular connection means for imposing an angular position on the slide rod relative to the strut.

Abstract: A drive roller (1) comprising: a central hub (4); a body (5) extending around the central hub, the body (5) being made of a deformable material; a deformable band (8) extending over a circumference of the drive roller; and first rigid fins (17) and second rigid fins (18) arranged in alternation and extending radially inside the body (5), each first fin presenting a proximal end (17a) fastened to the central hub, and each second fin presenting a distal end (18b) that extends in the proximity of the deformable band.

Abstract: Aircraft landing gear (100) provided with a bottom portion (110) that is steerable by means of a steering actuator (1) comprising a toothed wheel (70) that is secured to the steerable bottom portion (110) and that co-operates with a rack (20) that is movable in translation along an axial travel axis (X) and that has ends (21a, 21b) connected to pistons (30a, 30b) mounted to slide in respective cylinders (10a, 10b). Each connection between one of the pistons (30a, 30b) and the associated end of the rack (20) presents play (J) at least axially, and possibly also angular play (E), and at least one sealing gasket, referred to as an internal gasket (25), between the rack (20) and a piston (30a, 30b), the gasket being arranged to oppose movements of the rack (20) relative to the pistons (30a, 30b).

Abstract: A roller (1) comprising: rigid reinforcement (4) defining a hub (5) for rotation of the roller about an axis of rotation X and a plurality of bars (6) regularly arranged around the hub (5) and extending parallel to the axis X; and bushings (10), each engaged on a respective one of the bars (6) and each comprising an outer rigid ring (11) surrounding a bushing body (12) made of deformable material.

Abstract: A machining system (10) comprising a machine comprising: real tool (12); actuators (14) for moving the real tool (12); sensors (15) for generating positioning data (16) for the real tool (12); a memory (17) for storing shape correction data (20) for the real tool (12); and a physical controller (18) for executing a machining program (19) and for controlling the actuators (14) as a function of the shape correction data (20), so as to move the real tool (12) relative to the real blank (13). On the basis of said data (22) representative of the positions of the real tool (12) and of the real blank (13), image display means (24) generate a reconstituted image (25) representative: of the shape of the real blank (13); and of the position of the real tool (12) at a given instant.

Abstract: The invention provides a device (2) for guiding a cable (8a, 8b) in a duct (4), the device (2) being characterized in that it comprises at least one guide tube (12) receiving the cable (8a, 8b) and at least one expandable clamp (13) secured to one end (12a) of the tube (12), the expandable clamp (13) being deployed so as to be blocked against the inside wall of the duct (4) in order to hold the tube (12) in the duct (4). The device serves to guide and hold the cable in the duct without damaging the duct.

Abstract: Subjecting an aluminum or aluminum alloy substrate to anti-corrosion and anti-wear treatment that is applicable in particular in the field of aviation for protecting certain mechanical parts of airplanes or helicopters that are subjected simultaneously to corrosion and to wear, including applying to the substrate, a sol-gel treatment step forming a sol-gel layer; and after the sol-gel treatment step, a hard oxidation step forming a hard oxide layer.

Abstract: A brake actuator comprising a sleeve (1), a piston (3) sealingly slidably mounted in the sleeve to apply a braking force, the piston being provided with an internal cage (21), and a wear compensating device (10) which defines a retracted position of the piston in the sleeve by means of an axially mobile stop which is able to be moved forward by the piston during the application of a braking force and/in frictional relationship with a fixed part (12) of the wear compensating device attached to the sleeve. The mobile stop comprises a radially deformable bushing (16) which cooperates with an olive (15) which is attached to a distal end of the fixed part of the wear compensating device. The bushing comprises means for guiding its proximal end (17) against an internal face of the internal cage (21).

Abstract: A braking actuator for a hydraulic aircraft brake, received in a cavity of a ring of the brake. The actuator comprises a liner structure (1) sealed in the cavity of the ring, and a piston (3) slidably mounted in the liner structure to apply a braking force. A wear-compensating device (10) defines a retreated position of the piston in the liner structure by an axially movable stop (11) which can be advanced by the piston during the application of a braking force and in frictional relationship with a fixed part (18) of the wear-compensating device secured to the liner. An elastic member (24) returns the piston to the retreated position defined by the piston bearing against the movable stop, the movable stop being in frictional relationship with the fixed part via at least one telescopic intermediate element (16) interposed between the movable stop (11) and the fixed part (18).

Abstract: An electromechanical actuator comprising an actuator member and an electric motor (2) adapted to drive the actuator member. The electric motor (2) comprises a rotor portion (4), a stator portion (5) comprising a yoke-forming body (9) and a set of coils received in slots (12) in the body (9), and at least one electrical module (17). The electrical module is adapted to generate an electrical power supply current (Ia) for the electric motor (2), which current flows in the set of coils. The electrical module (17) is carried by the body (9).

Abstract: A control method for controlling an electric motor driving rotation of an aircraft wheel (4a, 4b) for generating a torque command for controlling the motor, the method being characterized in that it comprises implementing: a first servo-control loop (23) having as its input signal a speed setpoint, having as its return signal a signal representative of the speed of the wheel or of the aircraft, and having as its output signal an acceleration setpoint (Cons_a); and a second servo-control loop (24) having as its input signal the acceleration setpoint (Cons_a), as its return signal a signal representative of the acceleration (Ar) of the wheel or of the aircraft, and as its output signal the torque command.

Abstract: A circular needling table for needling a textile structure made from an annular fiber preform, includes: a horizontal top on which an annular fiber preform is to be placed; a driver system constructed and arranged to drive the fiber preform in rotation about a vertical axis of rotation; and a needling device for needling the fiber preform, the device including a needling head extending over a predetermined angular sector of the table top and to be driven with vertical reciprocating motion relative to the table top, and a mover system constructed and arranged to move the needling head in a direction that is radial relative to the axis of rotation of the fiber preform.

Abstract: An aircraft electromechanical braking system comprising a braking control unit 10 and at least one electromechanical brake 1, the brake 1 being fitted with at least one electromechanical actuator 4 having a pusher 6 suitable for being moved by means of an electric motor 7. The actuator 4 also has a blocking member 8 for blocking the pusher 6 in position. The control unit 10 is adapted to cause the braking system to operate in an additional braking mode referred to as “combined” mode, in which the motor 7 is activated to bring the pusher 6 into a position in which it exerts a given holding force, and then the blocking member 8 is activated, while activation of the motor 7 is maintained.

Abstract: An aircraft undercarriage comprising a telescopic linear rod (0, 0?, 0?) comprising first and second sliding rod portions. The undercarriage further comprises: a first permanent magnet set (1a, 1a?, 1a?) fastened to the first rod portion (1, 1?, 1?); and a second permanent magnet set (2a, 2a?, 2a?) fastened to the second rod portion (2, 2?, 2?); the first and second permanent magnet sets (1a, 1a?, 1a?, 2a, 2a?, 2a?) generating a magnetic repulsion force between the first rod portion (1, 1?, 1?) and the second rod portion (2, 2?, 2?) and maintaining a first annular space (E1) between the first rod portion and the second rod portion.

Abstract: An aircraft wheel which is provided with rotational driving unit (110). The driving unit comprises a driving ring (111) which is associated with structure (112) for attaching the ring to a rim of the wheel. The attachment structure is fixed to treads (119) of the rim which further serve to retain removable brake blocks (121) with which the rim is provided.

Abstract: The invention relates to fiber reinforcement for making an elongate mechanical part (10) out of composite material having a lug (14) at at least one end for receiving a pin for making a pivot connection with another part, the fiber reinforcement being made from a central fiber structure (106; 106?) for forming a core that is obtained by three-dimensional weaving, from a peripheral fiber structure (16; 16?) that is to form a belt surrounding the central structure so as to form at least one empty cylindrical space in the lug of the part, and from at least one annular fiber structure (112; 112?; 112?) that is to form a ring that is formed inside the empty space provided between the central structure and the peripheral structure.

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: 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 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: 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.