Abstract: Method for estimating the damage to rotational driving actuators of the wheels borne by aircraft undercarriages, the method comprising according to the invention the steps of: In service, recording data relating to the driving actuators, in particular data on torque developed by the driving actuators, on speed of rotation of the motors of the driving actuators, on number of revolutions of the motors; Deducing therefrom damage undergone by the driving actuators; Estimating a remaining life of the driving actuators.

Abstract: Architecture of an aircraft braking system having a brake (20) comprising a plurality of electromechanical actuators (25), with each electromechanical actuator (25) comprising a power module and a digital communication module (26). The brake digital communication modules are interconnected to form a digital network (30). The system also has two control units (22a, 22b) adapted for generating digital signals for controlling electric motors and one network interconnection member (23) connected to two control units and incorporated in the digital network for distributing the digital control signals to the digital communication modules via the digital network.

Abstract: The invention relates to a method for linking an end (9) of a shaft (8) of a tachometer (7) positioned in a landing gear hub (1) and a wheel (2) mounted to rotate on said hub, the method comprising the step of equipping the wheel with a housing (14) suitable for receiving the end of the shaft of a tachometer and driving the shaft in rotation with the wheel, the housing comprising a bearing member (17) protruding inside the housing to be pushed back by the end of the shaft against an elastic member (18) to take up any play between the end of the shaft and the housing. The invention also relates to a bush ensuring application.

Abstract: An aircraft undercarriage having a sliding rod slidably mounted in a strut-leg, and a scissors linkage (4) having one branch (4a) hinged to the strut-leg or to a turning element of a control for steering the sliding rod mounted to turn in the strut-leg, and one branch (4b) hinged to the sliding rod, the branches being hinged to each other by a pivot pin (12), the undercarriage being fitted with a shimmy-attenuator device (10a, 10b) placed on the pivot pin of the shimmy-attenuator, the attenuator device including threshold resilient return means generating a force returning the branches towards a rest position, and at least damping means generating a damping force when the branches move axially along the pivot pin. The attenuator device comprises two modules (10a, 10b) placed on either side of the scissors linkage in order to co-operate with the pivot pin, each of the modules performing at least one of the damping function and the threshold resilient return function.

Abstract: The invention relates to a method for adapting a stop that is adjustable by screwing onto the extremity of a fine tube (1), including the following stages: slipping onto the extremity of the tube (5) a ferrule (10) that is threaded on its external surface and is immobilized on the extremity of the tube by means of a plurality of pins (8) engaged in orifices (7,9) facing towards the ferrule and the tube; screwing onto the ferrule a nut (14) having a first end face (15) acting as a stop in order to preload any element (4, 4) mounted on the tube in front of the ferrule, and a second opposing end face (18) containing forms (25) adapted for it to be driven in rotation by a tool, the nut covering the pins in service.

Abstract: A method of forming an aerospace component, the method including: forming a first subcomponent by an additive layer manufacturing (ALM) process, the first subcomponent having an inner surface defining an inner space; performing a non-ALM machining process to modify a portion of the inner surface of the first subcomponent; and forming a second subcomponent by an ALM process, the second subcomponent being arranged to close the inner space to complete the component.

Abstract: A phantom for use in quality control of tomographic images, the phantom including a cylindrical plate made of a uniform material having a density d1, with two cylinders being inserted in the plate, the cylinders being made out of uniform materials having different densities d2, d3, the density of one of the cylinders being greater than the density d1 of the plate, and the density of the other cylinder being less than the density d1 of the plate, and including a first series of pairs of holes of different diameters drilled in the plate, the axes of the holes of the first series being oriented axially relative to an axis of revolution of the plate, and the holes in a given pair being spaced apart from each other by a distance equal to their diameter.

Abstract: An aircraft landing gear assembly having a main strut and an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on a mounting pin and arranged to define a brake rod anchor point. The adaptor member is coupled to a part of the landing gear assembly so as to react brake torque and can be formed from a different material than a portion of the main strut.

Abstract: An aircraft landing gear shock absorber having an inner housing portion slidably coupled within an outer housing portion, and a chamber which defines a sealed fluid volume for containing shock absorber fluid within the shock absorber. The chamber includes a moveable wall portion arranged to move between a first position and a second position, and in the second position the effective volume of the chamber is decreased such that the shock absorber fluid pressure increases, to provide a bump to the shock absorber.

Abstract: The invention relates to an aircraft wheel comprising a hub (52) for mounting the wheel on a landing gear axle to enable the wheel to rotate about an axis of rotation, and a rim (55) with edge flanges for receiving a tire, the rim being secured to the hub by a web (56). The hub is adapted to receive releasably a bearing box (60) comprising two bearings (53, 54) each having an inner ring and an outer ring mounted between a bushing (61) for engaging on the axle with an outside wall shaped to receive the inner rings of the bearings, the bushing having one end (63) shaped as an abutment and another end shaped to receive a pre-loading nut (67); and a sleeve (62) extending around the bushing and having an inside wall presenting two shoulders to hold the outer rings of the bearings axially, the sleeve having an outer wall shaped to be received as a sliding fit in a bearing of the hub, with one end (68) shaped as an abutment and another end shaped to receive a stop nut (70).

Abstract: The invention relates to a method for connecting in rotation an output member (5) of an electric motor (1) and an element (2) that is to be driven in rotation, comprising the use of at least one fusible pin (11) that links the output member and the element that is to be driven, and that has at least one section that is prone to fail in shear when a torque transmitted by the fusible pin exceeds a predetermined threshold. The method comprises the step of interposing, between the pin and either the output member or the element that is to be driven, at least one elastic member (20) comprising a first travel with a first stiffness followed by a second travel with a second stiffness greater than the first stiffness.

Abstract: Aircraft landing gear (1) comprising: an axle shaft (2); a strut (3) extending along a main strut axis (Z) and having a first part (3a) carrying the said axle shaft (2) and a second part (3b); a main damper (5) designed to damp axial movements of the first strut part (3a) with respect to the second strut part (3b); a first secondary damper (6a) distinct from the said main damper and designed to damp a movement of angular oscillation, about the axis (Z). The first secondary damper (6a) is carried by the first strut part (3a) and comprises: an inertial mass (M); and means (7a) of connecting the inertial mass (M) to the first strut part (3a) which means are designed to damp rotational movements of this inertial mass (M) about the axis (Z).

Abstract: A method of reducing the cooling time of disks of a brake (5) of an aircraft wheel (1) fitted with a heat screen (10) extending between the wheel and the disks of the brake and mounted to rotate on an aircraft undercarriage about an axis of rotation, the method including making obstacles (11) on the heat screen, which obstacles project from a face of the heat screen that faces towards the brake disks.

Abstract: The invention provides a method of reducing the cooling time for disks of a brake (5) of an aircraft wheel (1) fitted with a heat screen (10) extending between the wheel and the disks of the brake, and mounted to rotate on aircraft landing gear about an axis of rotation, the method comprising making perforations (11, 12, 13) through the heat screen to allow air heated by the disks to pass through the heat screen towards the wheel, the perforations being provided with obstacles to block any radiation from passing directly from the disks towards the wheel.

Abstract: An aircraft braking system comprising: a first group (Ga) of actuators and a second group (Gb) of actuators. A first control module (105a) is adapted, in a nominal mode, to control the first group, and in a reconfigured mode, to control the first group and the second group. A second control module (105b) is adapted, in a nominal mode, to control the second group, and in a reconfigured mode, to control the first group and the second group. A monitoring unit adapted is adapted to monitor the first control module and the second control module, and to put the first control module into the reconfigured mode of operation when the monitoring unit detects a failure of the second control module, and to put the second control module into the reconfigured mode when the monitoring unit detects a failure of the first control module.

Abstract: A bistable linear electromagnet comprising a first housing (10) and a second housing (11) in alignment, a movable armature (18) comprising a rod (19) and a shuttle (20) that is slidably mounted, and a first coil (13) positioned in the first housing and a second coil (15) positioned in the second housing. A cavity (25) is made in a measurement wall (4) of one of the housings, and the electromagnet comprises a magnetic field sensor (26) positioned in the cavity and designed to measure a magnetic flux existing in a magnetic path formed by the walls of said housing and by the shuttle, in order to detect whether the shuttle has moved towards or away from the abutment wall of said first or second housing.

Abstract: The invention relates to an aircraft undercarriage having a leg (2) pivotally mounted on a structure of the aircraft to pivot about a pivot axis (X1) between a deployed position and a retracted position, the undercarriage including a foldable brace (3a, 3b) comprising two hinged-together elements, one of which is hinged to the leg and the other of which is hinged to the structure of the aircraft, in such a manner that when the leg is in the deployed position, the two brace elements are locked together in a substantially aligned position, the undercarriage also being provided with a rotary drive actuator (10) having an outlet shaft acting on one of the elements of the foldable brace in order to cause the leg to pivot between its two positions.

Abstract: A method of controlling an aircraft electrical taxiing system, the method comprising the steps of: defining a target value (Ld_nmax) for an electrical parameter; generating a nominal force command (Cmd_nom) for the electrical taxiing system; in parallel with generating the nominal force command (Cmd_nom), using a processing system (2) to produce a maximum command force (Force_max) for the electrical taxiing system so that a real value of the electrical parameter reaches the target value (Ld_nmax), the processing system (2) comprising a regulator loop (4); and generating an optimized force command (Cmd_opt) for the electrical taxiing system equal to the smaller of the nominal force command and the maximum command force.

Abstract: An aircraft wheel including a rim (2) comprising two assembled-together rim halves (3a, 3b), each rim half (3a, 3b) having a bearing surface (7) extending in a plane perpendicular to an axis of rotation (X) of the aircraft wheel. The aircraft wheel further includes a spacer (9) situated between the two bearing surfaces (7) when the rim halves (3a, 3b) are assembled together.

Abstract: A device for measuring a relative rotation speed and/or a relative angular position between a first rotating element (2) and a second rotating element (3). The device includes a structure for generating a magnetic field rotating at a magnetic rotation speed representing a rotation speed of the first rotating element and a sensor (5) mounted to rotate and adapted to produce from the rotating magnetic field a measurement signal representing the relative rotation speed and/or the relative angular position. The device also has a processor (11) positioned on the static part and intended to acquire the measurement signal. A transmitter is adapted to transmit the measurement signal to the processor from the sensor.