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: 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: 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.

Abstract: The invention relates to an actuator including an electrical machine. The electrical actuator (100) comprising: a polyphase machine (101); at least one connection member (143) for powering the actuator from at least one network (146) delivering alternating current; and first and second buses (106, 107) connected in parallel between each connection member (143) and the machine (101) for applying frequency control thereto. Each inverter (111, 131) comprises a plurality of arms each having two controlled switches, each phase of the machine (101) being connected both to the two switches of an arm of the first inverter (111) and also to the two switches of an arm of the second inverter (131). The actuator further comprises controlled connection and disconnection means interposed between each bus (106, 107) and each connection member. The invention is applicable to actuators used in aviation.

Abstract: The invention relates to an architecture for powering aircraft brakes for an aircraft having at least two undercarriages, each having a certain number of wheels, each of the wheels being fitted with brakes, each having a certain number of electromechanical braking actuators, the architecture including controllers for delivering power signals to the actuators in response to a braking order, the wheels on each of the undercarriages being grouped together in first and second complementary groups such that for each group of wheels, a first group of actuators is controlled by one controller that controls those actuators only, and a complementary second group of actuators is controlled by another controller that controls only those actuators.

Abstract: The invention relates to a method of braiding reinforcing fibers on a mandrel (8) with a machine having a ring (9) carrying at least two series of reels of fibers, by moving the mandrel at a predetermined forward speed while moving the two series of reels along the ring (9) so that they cross while rotating in opposite directions and at a predetermined speed of rotation about an axis (AX) of the ring, the braid being formed on the mandrel (8) in the vicinity of a region of convergence (R) of the fibers that together define a conical shape (C), the method being characterized in that it comprises: a step of reconfiguring the machine in which the angle (a2) at the apex of the cone (C) defined by the fibers takes on a new value (a2); and a step of restarting braiding in which the movement of the reels along the ring (9) and the forward movement of the mandrel (8) are re-established with a new speed of rotation and a new speed of advance.

Abstract: The invention relates to a method of managing movement of an aircraft on the ground, the aircraft including at least one left main undercarriage and at least one right main undercarriage, each comprising wheels associated with torque application members for applying torque to the wheels in response to a general setpoint, the general setpoint comprising a longitudinal acceleration setpoint and an angular speed setpoint, the method including the successive steps of braking down the general setpoint into general torque setpoints for generating by the torque application members associated with each of the wheels.

Abstract: A brake for an aircraft wheel comprising an actuator-carrier 14 that carries at least one electromechanical actuator 15 having a pusher 19 that is movable along a direction parallel to an axis of rotation X of the wheel 2 and facing friction elements 7, 10 in order to apply a braking force selectively against the friction elements 7, 10. The actuator-carrier 14 and the actuator 15 include guide means 25, 32 for guiding the actuator 15 while being installed on the actuator-carrier 14 in a radial direction Y until it reaches a service position. The guide means forms a bearing surface for transmitting braking forces from the actuator to the actuator-carrier. Position-holder means 37 holds the position of the actuator in its service position and comprises a strap 37 fastened to the actuator-carrier 14 to prevent the actuator 15 from moving on the actuator-carrier 14 in the service position.

Abstract: The invention relates to a device for braking/driving an aircraft wheel mounted to rotate on an undercarriage axle, the device comprising: a stack of disks comprising disks that are constrained in rotation with the wheel and that alternate with disks that are constrained in rotation with a torsion tube; a support member mounted to rotate on the axle and constrained in rotation with the torsion tube; braking actuators carried by the support member for selectively pressing the disks together; and a drive member for selectively driving the support member in rotation; the support member carrying a secondary of a transformer having a primary arranged facing the support member while being stationary in rotation, the secondary being electrically connected to the actuators and the primary being adapted to being connected to a non-DC voltage source.

Abstract: The invention relates to a method of managing the braking of an aircraft 1 having at least one controllable brake 9 for braking the aircraft 1 when the aircraft 1 is on the ground and as a function of a braking setpoint C, wherein the method includes correcting the braking setpoint as a function of the pitch angle ? of the aircraft 1 during braking.

Abstract: An actuator comprising a body in which a rod is mounted to slide, the actuator including a screw extending inside the rod to co-operate with a nut secured to the rod, the screw being driven in rotation by a motor. The rod is associated with a piston that slides in a cavity of the body so as to define two chambers therein, the chambers being filled with hydraulic fluid and being put into communication via fluid transfer means fitted with at least one regulator member adapted to throttle the fluid expelled from one of the chambers, in at least one travel direction of the rod.

Abstract: A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network and a DC voltage of the energy storage element, the DC voltage of the energy storage element floating relative to the DC voltage of the high-voltage electrical network and centered relative to the mass of the aircraft, the module including an input module including two filters each capable of receiving a DC voltage, a first arm and a second arm including switches, and a mechanism controlling the switches, operating per cycle of a switching period and capable of controlling at least one first switch and at least one second switch identically but offset by a half-period, whereby the first switch is open when the second switch is closed and vice versa.

Abstract: The invention relates to a controlled-friction device comprising first and second elements mounted to move relative to each other in a sliding direction, wherein the device of the invention includes first and second friction members arranged symmetrically between the two elements in order to rub selectively against the second element, each of the friction members being urged towards a wedging position by a presser member, the first friction member being arranged, in a first direction of relative movement between the two elements along the travel direction, to tend to prevent relative movement between the two elements, and in a second direction to exert on the two elements an opposing friction force that depends on a stress applied against the first wedge member by the presser member; while the second friction member is arranged in the second direction to tend to prevent relative movement of the two elements, and in the first direction to exert on the two elements an opposing friction force that depends on a s

Abstract: A one-piece or otherwise unitary annular shim member made from a perforated metallic material is used to maintain a space between stacked annular preforms during a manufacturing process, such as densification. The metallic material used preferably can withstand at least the temperatures encountered during densification. The one-piece structure advantageously simplifies the arrangement of the preforms in a process chamber and causes less deformation in the preforms. In one example, the shim member is made from a metallic mesh and may utilize a crimped weave structure.

Abstract: A method of controlling power applied to an induction coil assembly used for densifying porous articles with a liquid matrix precursor. The control of applied power addresses dynamic changes in the electrical characteristics of the porous article being densified as it becomes denser. In particular, the power applied is controlled in accordance with changes in resonant frequency of the coupled system of the induction heating system and the porous article.

Abstract: The invention relates to a method for making a metal part that comprises a reinforcement (15) made of ceramic fibers. The method comprises the following steps: forming at least one annular-shaped insert (15) by assembling a bundle of metal-coated fibers; placing the insert into a hollow metal mold (10) such that the insert is spaced between the walls (10a, 10b) of the mold; filling the mold with a metal powder; generating vacuum in the mold and closing the same; hot isostatic compressing the assembly at a temperature and under a pressure sufficient for binding the powder particles between them and for binding the insert fibers between them; removing the mold and optionally machining to the desired shape.

Abstract: The invention relates to a method of powering at least one brushless DC electric motor having a plurality of phases for powering, the method including the steps of associating a static contactor with the motor for taking input voltage pulses and delivering polyphase voltage pulses to the motor in a manner that is servo-controlled to the angular position of the rotor of the motor, and for generating from a DC voltage source voltage pulses of frequency that is fixed and at a duty ratio that is controllable, thereby forming the input voltage pulses to the static contactor.

Abstract: The invention relates to a method of managing an aircraft having undercarriages carrying a certain number of braked wheels, the aircraft including: a system for operating the undercarriages including raising actuators and latching actuators for the undercarriages and the associated hatches; a braking system including braking actuators for braking the wheels of the aircraft; at least one control unit for controlling the operation of the undercarriages and the braking; and at least one maintenance unit for selectively controlling at least some of the actuators of said systems while the aircraft is in a switched-off state during maintenance operations on one or another of the systems. According to the invention, the method includes the step of activating the maintenance unit while the aircraft is not in the switched-off state in order to use the maintenance unit for actuating actuators connected to the maintenance unit, in particular in the event of a failure of the control unit.