Abstract: A method of managing the braking of an aircraft having landing gear with wheels fitted with friction brakes and with auxiliary brakes that enable energy to be dissipated by other than friction. The method comprises the steps of, (1) when braking is requested, testing the braking parameters to determine whether the aircraft is in a braking situation for which the friction brakes are not essential for providing the requested braking, and (2) performing the requested braking by giving priority to actuating the auxiliary brakes so long as the aircraft remains within the braking situation, and actuating the friction brakes only if the aircraft departs from the braking situation.

Abstract: A method of measuring the thickness of a coating layer of a workpiece, the layer being formed on a substrate of the workpiece. The method comprises several steps. First, feeding a probe alternating electrical signal to induction device in order to induce a magnetic field in the workpiece. Second, measuring at least one physical characteristic that varies as a function of the magnetic field induced in the workpiece. Third, determining first and second values of an indicator, the values being determined respectively from measurements of the physical characteristic taken when the electrical signal has first and second given frequencies. Forth, calculating the difference between the first and second values of the indicator and determining the thickness of the coating layer as a function of the difference and of predetermined data correlating: the difference between the values of the indicator; and corresponding values for thicknesses of the coating layer.

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 cooperate 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: The invention provides a method of mounting an aircraft wheel drive member (30) on an undercarriage having an axle (1) that carries the wheel and that is provided with a torque plate (3) having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support (10) that bears against an inside face of the torque plate opposite from its outside face against which a brake (2) is fitted, and of fitting the drive member on the support.

Abstract: The invention relates to an actuator comprising a cylinder (1) in which a rod (2) is mounted to slide, the actuator having a screw (8) extending inside the rod to co-operate with a nut (7) secured to the rod, the screw being driven in rotation by a motor (10), the actuator being characterized in that a hydraulic chamber (CH) filled with hydraulic fluid is arranged inside the actuator by means of a floating piston (20) sliding in sealed manner against the rod inside of the actuator, the hydraulic chamber being in fluid flow communication with an accumulator (21) via a solenoid valve (22) that is controllable between a closed state in which the chamber is isolated from the accumulator, and a fluid-passing state in which the hydraulic chamber and the accumulator are in communication, calibrated resistance being exerted against the passage of fluid from the chamber towards the accumulator.

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 undercarriage having a wheel mounted on an axle (3), a brake and a drive assembly. The brake comprises 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. The drive assembly is operative to drive rotation of the wheel and comprises 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: The invention relates to an aircraft wheel comprising a rim and a tire (20) received on the rim, the rim comprising two parts (1; 2) assembled with one another by means of assembly bolts (5), one of the parts comprising a recess (3) in which is arranged a seal (4) which is interposed between the two parts, the wheel being characterized in that at least one of the parts comprises at least one duct (6) extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tire, and on the other hand a space between the parts, the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent.

Abstract: The invention relates to an aircraft undercarriage intended to be mounted so as to be able to move on the aircraft between a deployed position and a retracted position, the undercarriage comprising a roller (1) carried by a support (4) secured to the undercarriage while being able to be moved with respect thereto, characterised in that the support is mounted pivotally on the undercarriage.

Abstract: A method for monitoring at least two aircraft wheel electromechanical braking actuators. For each electromechanical actuator, the method includes first determining a current value representative of the power supply current of the electromechanical actuator and determining a reference current value estimated from the power supply currents of at least one other electromechanical actuator. Then, the representative current value and the reference current value are compared. Any abnormal operation of the electromechanical actuator is detected when the difference between the representative current value and the reference current value is above a predetermined threshold.

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 sensor (1) comprising a casing (2) delimiting an internal volume (3) and having a passage (31) between the internal volume and a first external zone (Z1) external to the casing; a moving part (4) moveable inside the internal volume (3); detector (5) for detecting a movement of the 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), the groove (52) extending between the first external zone (Z1) external to the casing and the internal volume (3) internal to the casing. The sensor (1) comprises first sealing structure (14) positioned around the detection portion (51) inside the passage (31), the first sealing structure (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 the groove (52).

Abstract: A method of metal plating components includes placing a component and a spacer on a brochette, placing the brochette with the component and the spacer on a structure, and placing the structure with the brochette into a metal plating tank having a metal plating solution such that the component is submersed in the metal plating solution. The spacer is configured to mask a portion of the least one component and the component and the spacer are arranged on the brochette such that the spacer prevents the portion of the component from being contacted by the metal plating solution. The method also includes metal plating a surface of the component submersed in the metal plating solution, removing the structure with the brochette from the metal plating solution, drying the component on the brochette, and removing the dried component and the spacer from the brochette. Metal plating systems are also provided.

Abstract: A method of protecting a part made of carbon-including composite material against oxidation, the method including a) applying a coating composition on at least a portion of the outside surface of the part, the coating composition being in the form of an aqueous suspension including: a metallic phosphate; a powder of a compound comprising titanium; and a B4C powder; and b) applying heat treatment to the coating composition applied during step a) with a treatment temperature lying in the range 330° C. to 730° C. being imposed during the heat treatment in order to obtain a coating on the outside surface of the part, the coating including a first phase in which the metallic phosphate is in crystalline form and a second phase in which the metallic phosphate is in amorphous form.

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: An aircraft wheel having a rim having brake discs driving keys (21). The wheel has a rotational driver mechanism (210) which includes a drive gear (211) associated with coupling members (212) of the drive gear to the rim of the wheel. The coupling members are fixed to the rim by fixing members (220) introduced into orifices of the rim extending at an end of the keys which are also used to hold heat shields protecting the rim.

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: An aircraft wheel equipped with rotation-drivers (10) attached to clevises (19) projecting from a side of wheel rim (5). The rotation driver includes a ring (11) that is adapted to cooperate with a drive actuator and is provided with members (12) for attaching to the clevises in such a way that, between two attachment members, the ring forms a flexible and deformable segment.

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: Aircraft wheel rim in two parts, one of them a main part (1) comprising a hub (2), a disc (4) extending between the hub and an annular external portion (3) intended to accept a tire and shaped to have a flange (5) at one of its ends. The other end is shaped to accept the second part, a removable part (10) forming a flange (12) which removable part is attached to the annular external portion after the tire has been fitted. The rim has a structure for preventing the removable flange from rotating relative to the rim. The structure comprises at least one link (20) having ends, the centers of which define an axis which extends in a plane perpendicular to an axis of rotation of the rim while at the same time extending obliquely to make an angle (?) with respect to a radial direction, one of the ends being coupled to the main part and the other of its ends being coupled to the removable part.