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: 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: Aircraft landing gear including: a bogie beam coupled to a main strut; a first and second axles mounted on the bogie beam, each axle having a respective brake assembly and wheel assembly; and first and second stabilising arms mechanically coupling the first and second brake assemblies to respective first and second anchor points on the landing gear so as to react respective first and second brake torques generated as respective brake assembly applies a braking force to the respective wheel assembly. The first and second stabilising arms couple the respective first and second brake assemblies to the respective first and second anchor points such that the first and second brake torques result in both stabilising arms experiencing a tensile force or both stabilising arms experiencing a compressive force.

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 assembly for an aircraft, the landing gear assembly including: an elongate bogie beam; a first axle bearing having an outer part rotatably coupled to an inner part, the outer part being coupled to the bogie beam, the inner part including a mounting aperture; and an elongate axle provided through the mounting aperture of the inner part and coupled thereto, wherein the axle is coupled to the inner part of the first axle bearing in a configuration such that the longitudinal axis of the axle is spaced from the axis of rotation of the inner part, such that rotation of the inner part causes a change in the orientation of the axle relative to the bogie beam.

Abstract: An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is contacted and loaded by the first load bearing member (10) when it is loaded beyond a load limit. Preferably, the first load bearing member (10) has a yield point below the load limit and takes a permanent set once the yield point has been exceeded. A lateral probe (18) cooperates with the first load bearing member as it moves towards the second load bearing member and in turn deflects an indicator member (20) which takes a permanent set when a yield point is exceeded. Ready inspection of the indicator member then reveals whether or not it has been bent.

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: An aircraft landing gear assembly includes a bogie beam, a landing gear strut and a stop. The landing gear strut has a first end arranged to be pivotally coupled to an aircraft and a second end pivotally coupled to the bogie beam. The stop is arranged to limit pivotal movement of the bogie beam relative to the landing gear strut The stop includes an elongate member arranged to be deflectable in bending when the bogie beam reaches a pivotal limit.

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).

Abstract: A mechanical position indicator for providing a visual indication that a first part of an aircraft landing gear has assumed a predetermined position relative to a second part, the position indicator being arranged to be coupled to a first one of the first and second parts and in a first state arranged to hold an indicator element in a deployed position, the position indicator being arranged such that upon the first part assuming the predetermined position relative to the second part, a second one of the first and second parts changes the position indicator from the first state to a second state in which the indicator element is displaced from the deployed position, the position indicator being arranged to inhibit the indicator element thereafter returning to the deployed position.

Abstract: An independent drive device for an aircraft, the drive device comprising a motor member, a drive mechanism for driving an aircraft wheel, which is adapted to co-operate with the wheel to drive it for rotation, and a coupling mechanism interposed between the motor member and the drive mechanism to selectively couple the wheel to the motor member. The coupling mechanism comprises two coupling members of complementary shape, comprising a first coupling member that rotates with the drive and a second coupling member that rotates with the motor member. The independent drive device includes measurement device for generating information representative of a relative speed of rotation of the second coupling member and the first coupling member. The drive device is associated with a motor controller that causes the motor to rotate so as to cancel the relative speed of rotation between the coupling members prior to coupling them together.

Abstract: A hydraulic circuit for actuating an undercarriage, the circuit comprising: a feed line for feeding fluid and a return line; at least one door selector connected to the feed and return lines, the selector feeding door service lines, including an opening line and a closing line for opening and closing the doors; at least one undercarriage selector connected to the feed and return lines, feeding undercarriage service lines including a deployment line and a raising line for deploying and raising the undercarriage; and a door unhooking line and an undercarriage unhooking line. The door unhooking line is connected to at least one undercarriage service line while the undercarriage unhooking line is connected to at least one door service line, the circuit also including means for connecting the door service lines together during a door opening stage, and means for connecting the undercarriage service lines together during an undercarriage deployment stage.

Abstract: A fiber preform made of carbon fibers is densified with a carbon matrix in a plurality of separate stages. After a first densification stage and before the end of carbon matrix densification, ceramic particles are introduced in order to be dispersed within the composite material part. The introduced particles have a mean size of less than 250 nm and are made at least of a ceramic compound of an element selected from titanium, yttrium, tantalum, and hafnium, the ceramic compound being selected from oxides, nitrides, and mixed oxide, carbide, and/or nitride compounds that do not react with carbon at a temperature of less than 1000° C. and that have a melting point higher than 1800° C.

Abstract: There is described a landing gear having a bogie including a elongated beam (2) for accommodating at least two axles receiving each a pair of ground engaging wheels, at least one axle (5) being pivotally mounted on the elongated beam. The landing gear further includes axle travel limitation means (10) extending between said pivotable axle and said elongated beam to be hitched up thereto, said travel limitation means being deformable one way starting from an stable and lockable state thereof corresponding to a landing position of said pivotable axle. There are also described independently lockable and actuatable telescopic struts.

Abstract: The invention relates to a device for braking and driving rotation of a wheel (1) mounted to rotate on an aircraft landing gear axle, the device comprising: a torsion tube (26) adapted to be mounted to rotate on the axle that carries the wheel; a stack of disks (30) including first disks having means for constraining them in rotation with the wheel and second disks arranged in alternation with the first disks and including means for constraining them in rotation with the torsion tube; a ring (23) carrying braking actuators (24) that are adapted to act selectively to press the disks against one another, the ring being constrained in rotation with the torsion tube in order to form a rotary portion (20) of the device; a rotary drive member (40) for driving rotation of the rotary portion (20); and finally blocking means (51, 52) for selectively blocking rotation of the rotary portion, which means are independent of the rotary drive member.

Abstract: An aircraft landing gear assembly comprising a bogie beam (2), an axle (4) extending through the bogie beam and a jacking dome fitting (6) extending through a sidewall (8) of the bogie beam and arranged to transfer vertical loads applied to the jacking dome fitting to the axle.

Abstract: A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.