Abstract: A multifunction electromechanical device for an aircraft undercarriage. The device comprises a first shaft (10) mounted to rotate on the aircraft about an axis of rotation (R) that is substantially parallel to a hinge axis (X) of the undercarriage relative to the aircraft and a telescopic second shaft (20) mounted to rotate on the undercarriage extending downwards to the proximity of the wheels carried thereby. The device also includes a transmission (19) for transmitting rotary motion from the first shaft to the second shaft and a transmission (21) for transmitting rotary motion from the second shaft to at least one wheel carried by the undercarriage. With this configuration, if the wheel is not fitted with a brake, there is a specific brake (30) for braking one of the shafts relative to the undercarriage, and a motor (11, 15) for causing the first shaft to rotate.

Abstract: A controlled-friction device comprising a first element having a second element mounted thereon to slide in a sliding direction, and friction retaining means arranged to exert between the two elements an opposing force against relative movement of the two elements. The friction retaining mechanism comprises a friction member mounted securely to the first element to rub against the second element via a friction surface extending parallel to the sliding direction, a presser member for exerting a thrust force on the friction member, urging the friction member against the second element in a direction normal to the relative movement of the elements, and a linkage linking the friction member to the first element causing the friction member to separate from the second element during movement in either direction of the second element relative to the first element.

Abstract: Portable tooling for machining a bottom portion of an aircraft landing gear strut having a plurality of orifices. The portable tooling comprising a collar for positioning it on the bottom portion of the strut, at least one indexing member for angularly indexing the collar on the strut and for preventing it from moving, and a support that is removably fitted on the collar and that is fitted with a motor-driven machining spindle that carries a tool mounted to move on the support along a direction converging on the strut in order to machine an orifice extending in register with the tool. The collar is arranged in such a manner as to be capable of receiving the support in a plurality of angular positions, in each of which the tool extends in register with one of the orifices to be machined.

Abstract: An asymmetrical electric braking architecture for aircraft, having plural electro-mechanical brake actuators (EBAs) for selectively applying a braking force on friction elements of braked wheels. The architecture comprises (1) a brake control unit (BCU) for acting in normal mode to generate braking setpoint values in response to a braking order, (2) electro-mechanical actuator controllers (EMACs), each including at least one inverter for supplying power to the EBAs in response to the braking setpoint values, (3) at least one emergency brake power and control unit (EBPCU) including at least one inverter for supplying power to some of the EBAs in response to a braking order; and (4) protection means for channeling power supplied by the EMACs or the EBPCU towards the actuators while preventing power from being diverted towards the architecture.

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: A method of managing a ground connection of an aircraft having landing gear with wheels that are subjected to static loads, some of which wheels are fitted with respective braking devices and others are fitted with respective independent drive devices, the method including the step of causing a modification to a distribution of the static loading to which the wheels of the landing gear are subjected in such a manner as to: increase the loading on at least some wheels fitted with respective braking devices, during a braking stage; and increase the loading on at least some wheels fitted with respective independent drive devices, during an independent drive stage.

Abstract: The invention relates to an electromechanical braking method for an aircraft having at least one electromechanical brake 2 fitted to at least one braked wheel 1 of the aircraft, the brake 2 having friction members 3 and a plurality of electromechanical actuators 4, each actuator 4 comprising a pusher 5 suitable for being moved by means of an electric motor 6 to selectively apply a pressing force on the friction members 3. According to the invention, for a given braking operation, a total braking force to be applied against the friction members 3 of the brake is distributed in non-uniform manner amongst the actuators 4 of the brake, such that at least two actuators 4 apply respective different forces.

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: The present invention relates to a method of fabricating a metal link rod (6) that is longitudinally reinforced in its thickness by fiber reinforcement (2), the method comprising the following steps: making a metal blank including at least one longitudinal housing (11, 12) leading into an edge face of the blank; inserting fiber reinforcement (2) in the housing; connecting the fiber reinforcement to the blank by metal diffusion around the fibers of the fiber reinforcement (2); and finishing the blank in order to obtain a link rod (6). The invention also provides a link rod having a metal matrix in which reinforcing fibers are embedded that extend on either side of a longitudinal axis (X) of the link rod, the fibers leading into an edge face of the link rod.

Abstract: A process for manufacturing a metal part reinforced with ceramic fibers including machining at least one housing for an insert in a metal body having an upper face. At least one insert formed from ceramic fibers in a metal matrix is placed in the housing. The insert is covered with a cover. A vacuum is created in the interstitial space around the insert and the interstitial space is hermetically sealed under vacuum. The assembly, namely the metal body with the cover, is treated by hot isostatic pressure. The treated assembly is machined in order to obtain the part. The cover includes an element covering the insert in the slot and projecting from the upper face, and a sheet covering the upper face with said element. In particular, the insert is straight and the housing for the insert in the metal body forms a straight slot.

Abstract: The invention relates to a braking system architecture for an aircraft having wheels 1 braked by means of respective brakes 2, each brake having a plurality of electromechanical actuators 3a, 3b, the braking system having controllers 8a, 8b for distributing electric power Ps to the actuators 3a, 3b in response to a braking setpoint, each controller 8a, 8b being associated with some of the actuators of any given brake. According to the invention, each controller 8a, 8b has an input Ev for receiving information about the rotary speed of the wheel 1 braked by the actuators associated with said controller, the controller including processor means 13 for modulating the power transmitted to the actuators as a function of the speed of rotation of the wheel in order to provide anti-skid protection.

Abstract: The invention relates to an aircraft wheel comprising a rim adapted to receive a tire, and a hub connected to the rim (2) in order to receive bearings for guiding the wheel in rotation about an axis of rotation (X) on an axle of the aircraft, the wheel including at least one dog (10) that projects laterally from the rim in order to present two parallel faces (11) and that is pierced by an orifice (12) extending from one face to the other along a generally orthoradial direction (Y).

Abstract: A method of manufacturing an elongate insert configured to be integrated by CIC in a metal container, including coated yarns bonded together, the coated yarns being formed from metal-coated ceramic fibers. The method includes placing the coated yarns side by side in a bundle and pulling the fiber bundle through a shaping element so as to compact the fiber bundle transversely while forming the fiber bundle so as to have a defined cross section. A metal part incorporating a fibrous insert can be manufactured by the CIC technique.

Abstract: A braking system for an aircraft with electric brakes comprising plural electromechanical actuators (2). The system comprises a braking control unit (20) delivering a normal braking setpoint (21) for one or more controllers (10) of the actuators, and selection logic (15) for causing the braking system to operate in a plurality of modes. The system includes: a normal braking mode where the control unit generates a normal braking setpoint (21) for the controller(s); an ultimate braking mode, having priority over the normal braking mode, being responsive to a parking control member, and controlling actuators to respond to the actuation of the parking control member; and a parking braking mode, applied in response to the parking control member and only if the aircraft is stationary, in which the actuators are controlled to apply a force in response to the parking control member being actuated and are then blocked in position.

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: A device for spreading a cable of carbon fibers or carbon yarns, includes a disk mounted on a rotary shaft and provided with at least one comb adapted to comb a cable of carbon fibers or carbon yarns in a direction substantially parallel to the longitudinal direction of the fibers or yarns of the cable. The comb includes a plurality of teeth protruding radially toward the outside of the disk, and a device for rotating the disk around its rotary axis. Furthermore, a method for spreading a cable of carbon fibers or carbon yarns, includes at least making the teeth of the comb of the device flush with the cable in a direction substantially parallel to the longitudinal direction of the fibers or yarns of the cable.

Abstract: The invention provides measurement equipment for measuring the inflation pressure of a tire of a vehicle wheel 1, the equipment comprising: a body 16 defining an internal volume; a communication orifice 19 for putting the inside volume of the body 16 into communication with an inflation chamber situated between a rim 2 and a tire of the wheel and containing an inflation gas; an indicator member 25 slidably mounted in the body 16 so as to define a gastight separation between a first chamber 26 containing a given quantity of a reference gas and a second chamber 27 into which the communication orifice 19 leads, such that the indicator member 25 is subjected to opposing pressures that exist in each of the chambers; and position-identification means 30 for identifying the position of the indicator member in the body.

Abstract: A method of controlling a yawing movement of an aircraft running along the ground, the aircraft comprising at least one first landing gear with a steerable bottom part bearing wheels. The method comprises the steps of (1) on the basis of a yaw rate setpoint {dot over (?)}c, determining a wheel-steering prepositioning angle ?p; and (2) using closed-loop control which as its input has the yaw rate setpoint and which generates a command to steer the bottom part in order to steer it through a steering angle ?c equal to the sum of this prepositioning angle ?p and of an angle ?z which is determined taking account of an error between the yaw rate setpoint {dot over (?)}c and the measured yaw rate {dot over (?)}m when the steerable bottom part is steered by the steering angle ?c.

Abstract: A landing gear of an aircraft, including a strut including two arms forming a rotational axis for retracting the gear, a rotating tube mounted in a mobile manner such that it rotates inside the strut about a pivoting axis, a sliding rod that is mobile in a translatory manner in the rotating tube along the pivoting axis, and carries wheels of the gear at one of its ends, and at least one bearing point that is located on one of the elements of the gear at a distance from the retraction axis and can bear necessary efforts for the retraction, the bearing point being located on the rotating tube.

Abstract: In the field of aviation, a device for limiting aerodynamic noise from a deployed aircraft undercarriage during landing and/or takeoff. The device comprises two end plates (4a, 4b) for closing respective ends (2a, 2b) of a hollow pin (1) of the undercarriage, such as a hinge pin between two rods of the undercarriage, together with at least one tie (6) for engaging inside the hollow pin (1) to connect the two end plates (4a, 4b) together so as to hold them pressed against the ends (2a, 2b) of the pin (1).