Abstract: The invention relates to a method of managing a steering control for a steerable portion of an aircraft undercarriage, the method comprising implementing servo-control to servo-control an electromechanical steering actuator on an angular position setpoint, wherein, according to the invention, the servo-control implements a control relationship H? type, the position and speed information being delivered by means of a fieldbus of deterministic type to a computer that implements the servo-control.

Abstract: A circular needling machine for needling a textile structure formed from a helical fiber sheet, includes a needling table disposed beneath a feed table for feeding a helical fiber sheet for needling. The feed table includes a circular belt conveyor for receiving thereon a helical fiber sheet for needling, the conveyor being centered on a vertical axis and having a radial slot opening out under the circular conveyor to unwind continuously the fiber sheet received on the conveyor, the slot opening out under the conveyor towards a substantially straight chute that extends vertically between the conveyor and a support tray of the needling table centered on the vertical axis of the conveyor so as to take up the sheet unwound from the conveyor and bring it onto the needling table, the support tray having means for driving the fiber sheet in rotation about the vertical axis.

Abstract: A device for selectively connecting a tire to a pneumatic unit of an aircraft, the tire forming part of a wheel mounted to rotate on a hollow axle of the aircraft, the device comprising a stator and a rotor that is mounted to rotate relative to the stator and that includes a structure enabling it to be rotated by the wheel. The stator is bell-shaped and is designed to be received as a push-fit in the axle, and includes an end wall carrying a first pneumatic port for connection to the pneumatic unit via a tube running along the inside of the axle, the rotor extending substantially inside the stator.

Abstract: The invention relates to a braking system architecture for an aircraft fitted with electromechanical brakes including at least one electromechanical actuator. In accordance with the invention, the architecture comprises at least one proximity unit disposed in the proximity of the brakes at the bottom of the undercarriage and including input/output means for collecting and calibrating at least signals coming from sensors associated with the brakes, and for transmitting the signals as processed in this way to control members for controlling the actuators by means of a communications bus running along the undercarriage, the proximity unit further including control means for controlling the blocking members of the actuators.

Abstract: The invention relates to an aircraft landing gear of deformable-parallelogram type, including: a leg including a casing (1) having a lower end on which a rocker arm (3) carrying at least one wheel is hinged by means of a pivot (2), a shock absorber (5) being connected between the rocker arm and the casing; two panels (10, 11) each hinged on the one hand on the structure of the aircraft and on the other hand on the leg, about parallel axes; According to the invention, one of the panels (11) is hinged on the leg whilst being connected to the casing by a pin on one end of the pivot (2) of the rocker arm.

Abstract: The invention relates to a method of managing the steering of aircraft undercarriage wheels carried by a steerable bottom portion of the undercarriage, the bottom portion being associated with steering control including a steering member suitable for steering the bottom portion of the undercarriage in response to a steering order. According to the invention, the method comprises the steps of: monitoring the pressures of the tires carried by the wheels, and in response to detecting at least one of the following events: the pressure of one of the tires is less than a first predetermined threshold; and the difference between the pressures of two of the tires is greater than a second determined threshold; activating the steering control, if the steering control is not activated; and implementing a steering control relationship that is modified compared with a nominal control relationship used when the tires are properly inflated.

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 means (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 protecting an aircraft undercarriage (1) while it is being towed by means of a tow bar (13) hitched to a steerable bottom portion of the undercarriage, the method including the step of generating an alarm when a towing force imposed by the tow bar on the undercarriage reaches or exceeds a predetermined force threshold. The threshold is caused to vary as a function of an orientation of the steerable bottom portion of the undercarriage.

Abstract: The invention relates to a method of controlling the steering of a steerable portion of an aircraft undercarriage that is fitted both with a steering member for steering the steerable portion and also with at least two angular position sensors for sensing the angular position of the steerable portion in order to deliver respective signals representative of the angular position of the steerable portion, wherein the steering member is controlled by means of servo-control using information that is representative of the angular position of the steerable portion. According to the invention, the information representative of the angular position that is used is a mean of the angular positions sensed by the at least two angular position sensors.

Abstract: The invention relates to a method for making a connecting rod (6) made of a composite material and including a yoke (7) for receiving a mechanical axis, said yoke (7) including two parallel arms (7a, 7b) perpendicular to the mechanical axis, wherein the method comprises the steps of: making a mandrel (11) defining a single piece sufficiently rigid for receiving fiber layers (8a-8e, 9a-9d); applying onto said mandrel (11) base fiber layers (8a-8e) and additional layers (9a-9d) interleaved between the base layers (8a-8e) at the yoke (7, 7a, 7b) in order to form an additional thickness thereon; inserting lugs (13a, 13b) extending through the intermediate layers (9a-9d) and the base layers (8a-8e); injecting resin into the base layers (8a-8e) and the intermediate layers (9a-9d) and polymerizing said resin.

Abstract: The invention relates to a device (32) for rotationally coupling a wheel (10) with a ring (31) for driving the wheel (10) mounted so as to rotate coaxially with the wheel (10). According to the invention the device (32) comprises a plurality of connecting members (60) each extending in a direction contained in a plane perpendicular to the axis of rotation and forming an angle with a radial direction, the connecting members (60) being pivotably mounted on the one hand on the wheel (10) and on the other hand on the ring (31).

Abstract: The invention relates to a telescopic actuator comprising a body (1) defining a cylindrical cavity of longitudinal axis (X); a rod (3) mounted to slide telescopically in the cylinder along the said axis; a nut (7) secured to the rod; a lead screw (4) mounted on the cylinder to extend along and rotate about the said axis (X) and collaborate with the nut in such a way that a rotation of the lead screw causes a telescopic movement of the rod in the cylinder; means (8, 9, 10) for driving the rotation of the lead screw. According to the invention, the nut is mounted on the rod to be axially retained thereon by retaining means (12, 13, 14; 30 to 38) which can be made to release the nut axially from the rod.

Abstract: The invention provides an electromechanical actuator for a vehicle brake, the actuator comprising: a motor; a screw-and-nut system having a first element, the screw or the nut, rotated by the motor; and an antirotation member preventing rotation of the second element of the screw-and-nut system, the nut or the screw, so that the second element moves linearly in response rotation of the motor so as to exert compression selectively on friction elements of the brake. According to the invention, the actuator is subdivided into a first portion comprising the screw-and-nut system, and a second portion comprising the motor, the portions being designed to be separable while the actuator is mounted on a brake.

Abstract: The invention relates to a method for powering an autonomous drive device (4) in an aircraft comprising a certain number of drive motors (5) for the wheels (6) when the jet engines of the aircraft are not activated, the aircraft comprising an auxiliary power unit or APU (2) driving a first generator (1) for supplying power to devices on the aircraft that need to be powered when the jet engines are not activated, characterized in that the method comprises the use of a second generator (8) dedicated to the power supply of the autonomous drive device, the second generator being disposed in parallel with the first generator so as to be driven by the APU and, when it operates as a motor under the action of power recovered by the autonomous drive device, so as to help the APU drive at least the first generator.

Abstract: A method for efficient, industrialisable detection of machining burns of VHS steel. Machined steel is immersed in an aqueous solution of acids including hydrofluoric acid and nitric acid. To define a burn degree, a color chart for calibrating machining burns of VHS steel detected using the method is prepared. The color chart can include studs of the examined steel subjected to deliberate damage by excessive resurfacing actions (or other machining modes), then submerged in the acid solution. The resurfacing actions can be simulated by overheated thermal treatment, between an ageing temperature (for example 510° C. for steel) and a solution annealing temperature (950° C. for the steel). The samples are classified according to the grey level thereof resulting from the immersion and corresponding to a predetermined hardness and thus to a predetermined level of damage.

Abstract: The invention provides a method of managing the braking of an aircraft having a plurality of brakes comprising friction elements, the method comprising the following steps for at least one group of brakes: estimating an energy level (?E) to be dissipated by the brakes of the group; and estimating individual braking setpoints (Fi) for each of the brakes of the group so that the individual braking setpoints make it possible, at least under normal operating conditions of the brakes, to implement braking that dissipates said energy level, the individual braking setpoints also being determined so as to satisfy at least one other given operating objective.

Abstract: The invention relates to a method of fabricating a composite material part in which one or more layers of braided, or woven, or indeed draped reinforcing fibers are applied onto a mandrel having the general shape of a body of revolution. After one or more layers have been applied onto the mandrel, an operation is performed of winding at least one tie helically around and along the assembly constituted by the mandrel and each layer of reinforcing fibers that it carries, so as to press each layer of reinforcing fibers against the mandrel. The invention relates to fabricating composite material parts such as beams, connecting rods, or arms made out of carbon fibers.

Abstract: An aircraft braking system architecture having brakes with electromechanical actuators (3) for selectively applying a braking force to respective stacks of disks (2) in order to exert a braking torque on respective wheels. Included is at least one power module (7) that sends phase currents to the electromechanical actuators so that the latter can exert a braking force and at least one control module (8) for controlling the power module in response to a braking command such that appropriate phase currents are sent to the actuators so that these can develop the desired braking force. At least one power supply unit (20), comprising means (21) of generating a high voltage (HVDC), supplies the power module with the high power it needs for powering the actuators. The unit (20) also has means (22) for generating a low voltage (LVDC) for powering at least the control module at a low voltage.

Abstract: A method for distributing braking energy between a group of braked wheels 1 . . . p and fitted to N undercarriages of an aircraft, each of the braked wheels comprising a brake furnished with a stack of discs to which a load is selectively applied so as to generate a torque for braking the wheel. Each brake is equipped with means for measuring a thickness of the stack of discs, and in which: the setting C j = E j E 1 + … + E p . N . C is assigned as individual setting of braking to be generated by brake j. Here, p is the number of wheels concerned, C is the general setting of braking to be developed by the braked wheels of the same undercarriage, Ej is the thickness of the stack of discs of the brake of wheel j, and Cj the individual braking setting for wheel j. Each brake is controlled according to the individual braking setting thus determined.