Abstract: A detection method for detecting the blocked or unlocked state of a parking brake member including a bistable linear electromagnet (1) connected both to a power supply component (14) arranged to generate a control voltage (Uc) and also to a current sensor (15) arranged to measure the control current (Ic), the detection method comprising the steps of: controlling the power supply component (14) to generate a test voltage (Utest) across the terminals of the coil and thus generate a test current (Itest) flowing in the coil, the test voltage having an amplitude less than a predetermined voltage threshold so that a test magnetic field generated by the test current does not move the shuttle; acquiring measurements of the test current as produced by the current sensor (15); and analyzing the measurements of the test current and detecting the blocked or unlocked state of the parking brake member on the basis of this analysis.

Abstract: The invention relates to a hydraulic circuit for operating an aircraft landing gear comprising: a general valve (1) for admitting a supply pressure into the circuit; distributors (4, 6) for supplying undercarriages and/or landing gear doors operating actuators (3) or release actuators for hooks (5) maintaining the undercarriages and/or the doors in the retracted position; a depressurization valve (102) for, in an open position, allowing the selective distribution of supply pressure to an extension chamber (3A) or a retraction chamber (3B) of each operating actuator by the distributors, and, in a depressurization position, forcing the return of a retraction chamber of each operating cylinder. According to the invention, the depressurization valve is returned (105) in a stable manner to the depressurization position, and is moved into the open position only in response to the presence of supply pressure downstream of the general valve.

Abstract: The invention relates to a hydraulic actuator comprising a cylinder (1) in which a piston (2) secured to a rod (4) is mounted so as to slide in a sealed manner in order to delimit in the cylinder a hydraulic extension chamber (5) and a hydraulic retraction chamber (6) that are connected to respective ports, the hydraulic actuator comprising means for slowing the piston when the piston approaches a retracted position. According to the invention, the slowing means comprise first and second hydraulic lines (7, 8) extending between the extension port and the extension chamber, the first hydraulic line comprising a seat (13) while the piston bears a retractable finger (10) having an end (14) that comes to bear against the seat in order to close the first hydraulic line (7) when the piston approaches the retracted position, such that only the second hydraulic line (8) remains open while the piston completes its travel towards the retracted position. Landing gear and aircraft comprising such an actuator.

Abstract: A method of fabricating a friction part out of composite material, the method including densifying a carbon yarn fiber preform with a matrix including at least pyrolytic carbon and a ZrOxCy phase, where 1?x?2 and 0?y?1, the matrix being formed by film-boiling or by chemical vapor infiltration from a first precursor for pyrolytic carbon and a second precursor that includes zirconium, the second precursor being a zirconium complex including an alcoxy or carboxylate ligand bonded to zirconium.

Abstract: An aircraft undercarriage has an axle for carrying at least one wheel. The undercarriage further includes a magnetic measurement target and at least one magnetic movement sensor cooperating with the magnetic measurement target to measure bending of the axle. The magnetic measurement target has a body that extends inside the axle and includes a fastener end fastened to one end of the axle. The body also include a target surface that extends over an inside surface of the body. The magnetic movement sensor is positioned inside the axle to measure movement of the target surface.

Abstract: Hydraulic valves for dampening pressure spikes and associated methods are disclosed herein. In one embodiment, a hydraulic valve for dampening pressure spikes includes a valve body, a poppet at least partially inside the valve body, and a pilot piston at least partially inside the valve body and away from the poppet. The pilot piston contacts the poppet in response to a pressure spike.

Abstract: A telescopic actuator comprising a cylinder (2) in which a rod (3) is mounted to slide along a sliding axis (X), the actuator including a locking member comprising a locking finger (10) that is movable along a locking direction (Y) that is perpendicular to the sliding axis, between a locking position in which an end (9) of the locking finger (10) is engaged in a groove (8) of the rod in order to lock the rod in position, and a retracted position in which the end of the finger is disengaged from the groove in order to release the rod, a locking indicator (20) being secured to the locking finger to be movable between a position indicating locking when the locking finger is in the locking position, and a position indicating unlocking when the locking finger is in the retracted position, the actuator being characterized in that the locking indicator is secured to the locking finger by a connection (22, 23, 24) suitable for being interrupted in the event of the end of the finger being broken off while the rod is l

Abstract: An aircraft wheel comprising a hub for mounting the wheel on a landing gear axle for rotation, and a rim with edge flanges for receiving a tire, the rim being secured to the hub by a web. The hub receives releasably a bearing box comprising two bearings, each having an inner and an outer ring mounted between a bushing for engaging on the axle with an outside wall shaped to receive the inner rings, the bushing having one end shaped as an abutment and another end shaped to receive a pre-loading nut. A sleeve extends around the bushing and has (1) an inside wall with shoulders to hold the outer rings axially and (2) an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end shaped as an abutment and another end shaped to receive a stop nut.

Abstract: An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.

Abstract: An aircraft automatic braking system, comprising: a first functional module arranged in order to implement a state machine that includes a first branch comprising first states corresponding to a landing of the aircraft, a second branch comprising second states corresponding to a rejected take-off of the aircraft, and transitions, the first states, the second states and the transitions being defined independently of deceleration rates; a second functional module arranged in order to define a target deceleration of the aircraft at least on the basis of the deceleration rates and a current state of the state machine; and a third functional module arranged in order to define, at least on the basis of the current state and the target deceleration, an automatic braking command in order to control actuators of wheel brakes of the aircraft.

Abstract: An aircraft undercarriage comprising a shock absorber further comprising first and second portions that are mounted to slide telescopically relative to each other and that can come into internal abutment in the event of the shock absorber being compressed, the undercarriage being fitted with a detector device for detecting the shock absorber coming into internal abutment, which comprises firstly a punch secured to the first portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the first portion of the shock absorber, and secondly a sacrificial piece secured to the second portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the second portion of the shock absorber, the punch and the sacrificial piece being arranged in such a manner that, in the event of the two portions of the shock absorber coming into internal abutment, the punch strikes the sacrificial piece so as to form an indentation therein.

Abstract: An aircraft landing gear comprising at least an axle carried in the bottom portion of the landing gear, a wheel provided with a rim mounted on the axle of the landing gear via bearings in order to rotate about an axis of rotation, a brake threaded on the axle and including a torque tube extending around the axle, friction members mounted around the torque tube and extending between the torque tube and the rim of the wheel, and at least one brake actuator designed for selectively exerting a braking force on the friction members, the brake actuator being carried by an actuator carrier to which the torque tube is secured, and a rotary drive for driving the wheel in rotation comprising firstly an actuator for driving the wheel in rotation and secondly a transmission member for selectively transmitting movement in rotation from the rotation actuator to the rim of the wheel and extending between the axle and the torque tube.

Abstract: An electrical harness including at least one upstream connector arranged to be electrically connected to a computer, at least one downstream connector arranged to be connected to a complementary connector of an electromechanical actuator, and at least one electric wire electrically connecting the upstream connector and the downstream connector, the electric wire configured such that primary digital control signals produced or transferred by the computer travel over the electric wire via the upstream connector. The electrical harness may also include an electronic unit integrated in the electrical harness, the electronic unit configured to transform the primary digital control signals into analog control signals and to transmit the analog control signals to the electromechanical actuator via the downstream connector.

Abstract: The invention relates to a telescopic actuator comprising a cylinder (1) having a closed end (2) and an open end (3) for passing a hollow rod (4) mounted to slide axially in the cylinder.

Abstract: The invention provides a method of electrically powering an electromechanical braking actuator (1) fitted to an aircraft wheel brake, in which the power supply current (I) delivered to the electromechanical braking actuator is saturated to a saturation value (Isat) in order to limit the current consumed by the electromechanical braking actuator and thereby limit the forces developed by the actuator. The method includes the step of determining the saturation value (Isat) as a function of an internal temperature (T) of the electromechanical braking actuator while it is in operation.

Abstract: Method of controlling a braking device (100), the method comprising the following steps: receiving a braking torque instruction (If); on the basis of the received braking torque instruction (If), setting a first braking torque set point (Cf1) for a first brake (1) and a second braking torque set point (Cf2) for a second brake (2); measuring a first value of a first parameter (I8) representative of the first braking torque (C1) and modifying the first braking torque set point (Cf1) as a function of the first value with the aid of a first servocontrol loop (93); measuring a second value of a second parameter (19) representative of the second braking torque (C2) and modifying the second braking torque set point (Cf2) as a function of the second value (19) with the aid of a second servocontrol loop (94).

Abstract: A centre seeking actuator having an outer cylinder, a slave cylinder slidably disposed within the outer cylinder, and a rod assembly having a piston slidably disposed within the slave cylinder and a rod extending from the piston to a point outside the outer cylinder. One or more first dynamic seals are arranged to act on a side wall of the rod to inhibit working fluid leaking from the outer cylinder, and one or more second dynamic seals are arranged to act on a sidewall of the slave cylinder to inhibit working fluid leaking from the outer cylinder.

Abstract: Generally described, an architecture for an aircraft braking system is provided. The architecture includes a brake having friction members and electromechanical actuators, each electromechanical actuator having an electric motor and a power module; a computer arranged to produce digital control signals; a power unit arranged to produce an electrical power supply for powering the electric motors; and a junction box disposed on the undercarriage. The junction box may be configured to receive and to distribute the electrical power supply. The junction box generally includes an electrical motor control module that produces digital motor command signals from the digital control signals, and an electrical converter module that converts the digital motor command signals into analog motor command signals for the power modules of the electromechanical actuators.

Abstract: An electric braking system (1) for braking an aircraft, the system comprising: a brake (3) comprising an electromechanical actuator (5) designed so that when it applies a force to the friction members (4) that is less than or equal to a first maximum threshold, no degradation of the actuator occurs, and when it applies a force to the friction members (4) that is greater than the first maximum threshold, degradation is likely to occur; control means (7) configurable to occupy a first mode in which the controlled braking force cannot exceed the first maximum threshold, and to occupy a second mode in which the controlled braking force can reach the second maximum threshold; and configuration means (10) arranged to configure the control means (7) to occupy the second mode when in a situation preceding a potential interruption of takeoff (RTO) of the aircraft, and otherwise to occupy the first mode.

Abstract: The invention relates to guide tooling (22) for a circular needling table for needling a textile structure made from a helical fiber sheet, the tooling comprising an inner guide rail (24) of circularly arcuate shape, and an outer guide rail (26) of circularly arcuate shape arranged coaxially around the inner guide rail and connected thereto by radial reinforcement (28), the outer and inner guide rails defining between them a passage for guiding the helical fiber sheet under a needling head, the outer guide rail being made up of two outer guide rail angular sectors (26a, 26b) that are connected to each other by an outer actuator (28), the outer actuator being suitable for moving the adjacent free ends (26a-1, 26b-1) of the outer guide rail angular sectors apart from each other so as to expand the outer guide rail.