Abstract: A method for controlling an aircraft taxiing system, comprising the steps of: generating a nominal load command (Comm_nom); generating an acceleration setpoint (Cons_a); implementing, in parallel with the generation of the nominal load command, a processing chain (7) comprising a regulation loop (Br), the regulation loop (Br) having for its setpoint the acceleration setpoint (Cons_a) and for its command an acceleration command (Comm_a), the acceleration command being converted into an acceleration load (Eff_a), a maximum load threshold being equal to the maximum of the acceleration load (Eff_a) and a minimum load threshold (Seuil_min); and generating an optimised load command (Comm_opt) equal to the minimum of the nominal load command and the maximum load threshold.

Abstract: A landing gear (0) for an aircraft comprising a wheel (R), a system (1) for rotationally driving the wheel that is mobile between a clutched position and a safety position by passing through a declutched position, and a manoeuvring system (3) to displace the driving system (1) between its declutched and clutched positions. The gear comprises an elastic return (4) for returning the driving system (1) to its safety position and first and second abutments (51a, 52a) that are separated as long as the driving system (1) is away from its safety position and in contact with one another when the driving system (1) is in safety position. The first and second abutments (51a, 52a) oppose the passing of the driving system (1) from its safety position to its declutched position when the abutments are in contact with one another.

Abstract: Aircraft landing gear comprising an axle (100), a wheel (102) borne by the axle, a stack of discs (104) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator (106) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer (107) designed to bear the electromechanical actuator, the electromechanical actuator being fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component. Method of demounting a stack of discs from such a landing gear.

Abstract: Architecture of an aircraft braking system comprising: 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), with the brake digital communication modules being interconnected to form a digital network (30); two control units (22a, 22b) adapted for generating digital signals for controlling electric motors; 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 pivot connection type assembly comprising a shaft and first and second connection parts, each receiving the shaft so as to enable them to pivot relative to each other, the first connection part being arranged axially between a first end of the shaft and a radial plane, while the second connection part is arranged axially between said radial plane and the other end of the shaft. The shaft is hollow and includes an inside section that presents a radial dimension at least in a first axial plane and over a first segment of the shaft extending axially between the first end and the radial plane , which radial dimension varies, decreasing on axially approaching the radial plane. The assembly includes a ring interposed radially between the shaft and a bore of the first connection part, and presenting radial thickness that varies.

Abstract: Actuating system for an aircraft comprising: an electromechanical actuator (25) comprising a non-volatile memory (60) wherein stored data (61) including configuration data (62) specific to the electromechanical actuator is stored; a control unit (22) using the configuration data to implement a servo-control loop, the output signal of which is a digital signal controlling the electric motor of the electromechanical actuator; at least one digital transmission channel (50) connecting the control unit and the electromechanical actuator.

Abstract: Electric motor comprising a rotor and a stator (2), the stator comprising a body (3) forming a frame and a windings assembly (4, 5) housed in slots of the body. The electric motor comprises at least one rod (16, 23) used to connect, to one another, at least two fixed assembled parts of the electric motor, the rod extending into a housing (9) formed in the body over the entire length thereof in order to emerge on each side of the body.

Abstract: A method for ventilating discs (11) of a brake (10) fitted to an aircraft wheel (1) having a rim (2) mounted so as to rotate on an axle (4) of a landing gear of the aircraft. The brake discs are threaded onto a torsion tube (12) of the brake which extends around the axle. The method comprises the step of integrating a compressor (20; 30; 40) into a space extending inside the torsion tube in order to draw in air beneath the torsion tube and to return the air thus drawn in by the compressor over the torsion tube towards the brake discs.

Abstract: A linear telescopic actuator (1) comprising: a cylinder (2); a sliding part (3); a spring seat (4); and a first compression spring (5) capable of resiliently opposing the sliding part (3) approaching the spring seat (4). The spring seat (4) presents an outer annular groove (6) and the cylinder (2) includes an inner annular groove (7), the actuator (1) also presenting a blocking part (8), the actuator (1) being adapted to adopt selectively an assembled configuration and a disassembled configuration, the blocking part (8) in the assembled configuration being engaged inside the inner and outer annular grooves (6, 7), and the blocking part (8) in the disassembled configuration being disengaged from one of the grooves so as to allow spring seat (4) to slide in the cylinder (2).

Abstract: A method for measuring the rotation speed of a wheel including the steps of: acquiring an analogue measurement signal (Sma) generated by a magnetic tachometer and containing a useful signal the frequency of which is representative of the rotation speed of the wheel; digitizing in real-time the analogue measurement signal (Sma) in order to obtain a time-dependent digital measurement signal (Smnt); calculating a Fourier transform of the time-dependent digital measurement signal (Smnt) in order to obtain a frequency-dependent digital measurement signal (Smnf); and carrying out a frequency analysis in order to identify by a search for peaks a useful spectral line (16) so as to obtain the frequency of the useful signal and therefore the rotation speed of the wheel.

Abstract: A device for performing anodizing treatment on a part, the device including a treatment chamber including a part for anodizing together with a counter-electrode situated facing the part to be treated, the part to be treated constituting a first wall of the treatment chamber; a generator, a first terminal of the generator being electrically connected to the part to be treated and a second terminal of the generator being electrically connected to the counter-electrode; and a system for storing and circulating an electrolyte, the system including a storage vessel, different from the treatment chamber, for containing the electrolyte; and a circuit for circulating the electrolyte in order to enable the electrolyte to flow between the storage vessel and the treatment chamber.

Abstract: An aircraft undercarriage leg having an orientation control for wheels that causes a sliding rod to pivot. The orientation control has a rotating member mounted on the strut assembly having a toothed sector forming a pinion and is rotationally coupled to the sliding rod, and a rack mounted to slide on the strut assembly along a sliding axis perpendicular to the pivot axis to mesh with the pinion, the rack being moved by drive means. The drive include a rotary drive inside the rack adapted to turn about the sliding axis and to cooperate via a helicoidal coupling with the rack,. The rotary drive is immobilized axially by two opposite axial thrust bearings allowing angular tilting of the rotary drive. The thrust bearings are carried by at least one elongate support inside the rack having a proximal end fixed to an end of a cylinder in which the rack slides.

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.

Abstract: A landing gear (1) for aircraft comprising a first pair of first and second parts (7, 8, 7?, 8?), said first part (7, 7?) having a steel substrate and a sliding layer (C, C?) formed on this substrate, the second part (8, 8?) being in sliding contact against said sliding layer (C, C?) with a maximum rectilinear sliding amplitude (G, G?) of less than 0.5 mm, the sliding layer (C, C?) being adapted to support a surface pressure in excess of 50 MPa. The sliding layer (C, C?) is a zinc and nickel alloy comprising, in terms of percentage by weight of the alloy, between 12% and 18% nickel and the first part has a protective layer (P, P?) against corrosion extending from the sliding layer (C, C?), this protective layer (P, P?) being formed of said zinc and nickel alloy.

Abstract: Aircraft landing gear strut (1) comprising a main part (1a) extending along a main axis (X-X) of the strut and comprising an axle shaft (1b) extending in a plane (P) perpendicular to the main shaft (1a) of the strut, this axle shaft (1b) being designed to support at least one landing gear wheel (2a, 2b) equipped with brakes (3a, 3b) for braking the wheel, said axle shaft (1b) being made of steel. The axle shaft (1b) bears at least one layer of zinc-nickel alloy coating (C), this zinc-nickel alloy comprising, as a mass percent of the alloy, between 12% and 18% of nickel, at most 0.5% of elements other than nickel and zinc, the rest being zinc.