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: An aircraft wheel comprising two half-wheels (1, 2) assembled together by means of bolt fasteners (10; 110) clamping together disks of the half-wheels, each bolt fastener comprising a bolt (11; 111) with an end forming a screw head (12; 112) and a threaded end (13; 113) for receiving a nut (14; 114), the wheel also being fitted with drive keys (20; 120) that are fitted to one of the half-wheels for driving brake disks in rotation, the wheel being characterized in that each drive key has a first end (23; 123) that is shaped to co-operate with the screw head of one of the bolts so that said first end is held and prevented from moving when the key is in place on the wheel.

Abstract: A method of managing the braking of an aircraft, the aircraft having a plurality of wheels R1, . . . , R12, each fitted with a brake F1, . . . , F12 adapted to generate a braking force in response to brake pedals 5 being depressed. The management method comprising the steps of (1) distributing the wheels fitted with respective brakes in at least two distinct groups G1, G2, G3, G?1, G?2, G?3; (2) allocating respective braking relationships to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals; and (3) acting at predetermined intervals to permutate the allocation of the relationships to the groups in application of a predefined permutation relationship. The method also includes a step of modifying the permutation relationship in response to the occurrence of a predetermined event.

Abstract: The invention relates to a method of managing the braking of an aircraft, the aircraft having a plurality of wheels R1, . . . , R12, each fitted with a brake F1, . . . , F12 adapted to generate a braking force in response to brake pedals 5 being depressed, the management method comprising the steps of: distributing the wheels fitted with respective brakes in at least two distinct groups G1, G2, G3, G?1, G?2, G?3; and allocating respective relationships to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals. According to the invention, the method further comprises the step of modifying the distribution of the wheels in response to a predetermined event occurring.

Abstract: A method of fabricating a composite material part such as a link. The method comprises the successive operations of applying reinforcing fiber layers (14a, 14b, 14c) that are braided around a mandrel over all or part of the length of the mandrel, the layers being superposed one on another. The method includes a step of cutting an intermediate reinforcing fiber layer (14a, 14b, 14c) after it has been applied, a step of withdrawing a cut portion prior to applying the following braided layer (14b, 14c), thereby locally building up an extra thickness of reinforcing layers on each portion of the cut layer that has remained in place, the extra thickness constituting local reinforcement of the part. Resin is subsequently injected into the various braided layers prior to the resin being polymerized in order to prepare a blank. The method applies in particular to the field of aviation.

Abstract: An aircraft having wheels with hydraulically-actuating friction brakes and independent drives for driving the wheels in rotation and enabling the aircraft to move in stages of independent drive when engines of the aircraft are inactive. A main hydraulic circuit with a pressure source powers the brakes when the pressure source is active; with an alternative braking circuit for enabling the brake system at least when the engines of the aircraft are stopped. The alternative braking circuit includes an accumulator that is used for parking braking and is kept under pressure by the pressure source of the main circuit when the pressure source is active. An auxiliary hydraulic circuit pressurized by an auxiliary pump and power system enables the independent drives to be actuated. The auxiliary hydraulic circuit is connected to the alternative braking circuit to maintain an operating pressure in the accumulator of the alternative braking circuit.

Abstract: The invention relates to a method of managing a steering command for a steerable portion 3 of nose landing gear 2 of an aircraft 1, the method implementing servo-control to servo-control a steering actuator 6 to an angle position setpoint ?set for the steerable portion 3, the servo-control including calculating an error ? by subtracting a reference angle ?est from the angle position setpoint ?set. According to the invention, the reference angle ?est is an angle determined by calculation as a function of a longitudinal speed Vlong and a yaw rate ? of the aircraft 1.

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: 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 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: 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: A bearing assembly (2?) comprising a housing (3?) supporting first and second bearing ring portions (4, 4?) with bearing surfaces to engage an inner tubular member (1?) at axially spaced regions, characterized in that either: the bearing ring portions are provided by separate bearing rings (4?) supported in the housing member (3?) with bearing surfaces of different diameters; or the bearing ring portions are provided by a single bearing ring (4?) that is free to flex radially and is supported so that the second bearing ring portion is free to flex radially under load and its bearing surface than assumes a position with a greater diameter than that of the first bearing ring portion (4?).

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).