Abstract: Aircraft landing gear having a leg (12) for hinging to a structure of the aircraft so as to be movable between a deployed position and a retracted position, a main brace (15), a secondary brace (20), and a double-acting type unlocking actuator (30) having a first end coupled to the secondary brace and controllable for causing its links to move out of alignment against the action of the resilient member during retraction or deployment of the landing gear. The landing gear includes couplers (31, 33) for coupling to a second end of the unlocking actuator, which couplers ensure movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of its positions and tends to confirm said alignment when the landing gear is in its other position.

Abstract: A measuring tool (1) for measuring dimensional characteristics (D) of a production part (2). The tool (1) comprises a unit (3a, 3b) for positioning the measuring tool (1) relative to the part (2) and at least one measuring apparatus (4a, 4b) mechanically linked to the positioning unit (3a, 3b) by a mechanical link (5). The positioning unit (3a, 3b) comprises a first centring device (6a) for coming into contact against an inner surface (7a) of a first bore (22a1) of the production part (2) and a second centring device (6b) for coming into contact against an inner surface (7b) of a second bore (22b1) of the production part (2), the first and second bores (22a1, 22b1) being coaxial. The mechanical link (5) allows the relative displacement of the measuring apparatus (4a, 4b) relative to the first and second centring devices (6a, 6b).

Abstract: A method for rotationally driving an aircraft wheel, the wheel being equipped with a rim comprising two half-rims assembled by bolts (5). According to the method, a drive member for generating a torque for driving the wheel is controlled. The transfer of the drive torque to the wheel is accomplished via the rim assembly bolts.

Abstract: The invention relates to a telescopic actuator comprising a rod (4), a hollow lead screw (5), a fixed piston (9) comprising a first tail (10) which extends in the lead screw (5) and a head (11). According to the invention, the actuator comprises a first hydraulic connection channel (16) extending through the first tail (10) to fluidically connect a first chamber (C1) with a source of hydraulic fluid (17), and the channel (16) comprises first damping means suitable for slowing down the rod (4) when the latter is depressed by regulating a hydraulic fluid flow rate in the first channel provoked by the depression of the rod.

Abstract: The invention relates to an aircraft wheel comprising a rim and a tyre (20) received on the rim, the rim comprising two parts (1; 2) assembled with one another by means of assembly bolts (5), one of the parts comprising a recess (3) in which is arranged a seal (4) which is interposed between the two parts, the wheel being characterized in that at least one of the parts comprises at least one duct (6) extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tyre, and on the other hand a space between the parts, the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent.

Abstract: The invention relates to a method for managing an electric motor (6) intended to drive rotationally a wheel (4) of an aircraft (1), the method comprising the step of short-circuiting the phases of the electric motor (6) when the aircraft (1) is in a period of deactivation of the motor (6) during which it is envisaged not using the electric motor (6).

Abstract: The invention relates to an aircraft wheel comprising a rim and a tire (20) received on the rim, the rim comprising two parts (1; 2) assembled with one another by means of assembly bolts (5), one of the parts comprising a recess (3) in which is arranged a seal (4) which is interposed between the two parts, the wheel being characterized in that at least one of the parts comprises at least one duct (6) extending beneath the seal so as to establish a leakage path between on one hand a volume of gas delimited by the rim and the tire, and on the other hand a space between the parts, the path being nominally closed by the seal when the bolts are tightened correctly but allowing gas to leak from said volume when the bolt associated with said opening is not tightened correctly or is absent.

Abstract: The invention relates to a disc brake for an aircraft wheel, comprising friction discs (20,30), including rotor discs and stator discs, a structure comprising a torsion tube (11) on which the discs are fitted, a rear plate (12) which is located at one end of the tube, and a support (13) for braking actuators (14,15) at another end of the tube, the actuators being able to be selectively activated in order to apply a pressing force to the discs. According to the invention, the discs are separated into two groups, including a first group (20) which can be used alone for taxiing braking operations, and a second group (30) which can be used alone or in conjunction with the first group for take-off/landing braking operations.

Abstract: A method for monitoring a blocking member (12) of an electromechanical actuator (1). The monitoring method comprising the steps of: determining a value representative of a power supply current of a motor (11) during an off-load operating phase of the electromechanical actuator (1); comparing the value representative of the power supply current with a predetermined current threshold defined from nominal off-load operating characteristics of the electromechanical actuator (1); and detecting an accidental locking of the blocking member (12) when the value representative of the power supply current is above or equal to the predetermined current threshold. There also is an electromechanical actuator (1) comprising a blocking member (12) monitored by such a method.

Abstract: The invention relates to a steering actuator piston with a rack (6) for an aircraft landing gear (1) characterized in that the piston comprises a body (10) made of a lightweight alloy having an externally threaded main span (11) terminated on one side by a shoulder (12) and extended on the other side by a skirt (13), the body having screwed to it a tapped bronze bushing having on its outer wall at least one groove for receiving a seal, the skirt having a drilling to receive a pin for securing the piston to the rack, the bushing extending in service between the shoulder and the pin so that it is retained axially between the shoulder and the pin.

Abstract: An electromechanical actuator for a vehicle brake, the actuator comprising first and second portions 8 and 9 that are separable. The first portion 8 includes an electric motor 5 and connection structure 15 for connecting the actuator to an external control structure 4. The second portion 9 including a slidable pusher 6, the second portion 9 also including measurement structure 21. The first portion 8 includes a first antenna 14 connected to the connection structure 15, and the second portion 9 includes a second antenna 22 connected to the measurement structure 21, the two antennas 14, 22 being arranged to be electromagnetically coupled together when the first portion 8 and the second portion 9 are coupled together, so as to enable electrical signals to be transferred between the measurement structure 21 and the connection structure 15.

Abstract: A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20).

Abstract: A method of fabricating a connecting rod (6) out of composite material using three-dimensional fabric of woven reinforcing fibers, the connecting rod (6) extending in a main direction. The method comprises the steps of: cutting out one or more base pieces (7, 8) from a three-dimensional fabric; cutting out one or more reinforcing pieces (9, 10) from a three-dimensional fabric; installing the various pieces (7, 8, 9, 10) on a support in order to shape them; securing the various pieces (7, 8, 9, 10) to one another by stitching (12, 13, 14, 15) using reinforcing fibers in order to constitute a reinforcing fiber preform; installing the preform on a mandrel; and injecting resin into the preform and polymerizing the resin.

Abstract: A multifunction device for an undercarriage. The device comprises at least a first shaft rotatably mounted on the aircraft to rotate about an axis of rotation that is substantially parallel to a hinge axis hinging the undercarriage to the aircraft, and a telescopic second shaft rotatably mounted in the undercarriage and extending down along the undercarriage to the proximity of wheels carried thereby. A motor is adapted to cause the first shaft to rotate. The telescopic second shaft is a single shaft that extends inside the undercarriage to the proximity of an axle carrying the wheels of the undercarriage. The second shaft is connected to a differential connected to the wheels via drive shafts extending inside the axle.

Abstract: A landing gear that comprises an axle (2) and a wheel (3, 3?). The wheel comprises a rim (4, 4?) mounted so as to rotate on the axle about a first axis of rotation (X), first blocks protruding from a lateral face (F, F?) of the rim, the first blocks being adapted to cooperate with a gearwheel (8) of a drive actuator (7) carried by the landing gear. The gearwheel is mounted rotatably about a second axis of rotation (Y) perpendicular to the first axis of rotation.

Abstract: Aircraft undercarriage leg including an axle (3) that bears at least one wheel (4), the undercarriage leg being equipped with a unit (6) for driving rotation of the wheel, wherein the drive unit is rigidly fixed to the axle and a deformable support (12) extends between a cantilevered portion of the drive unit and a portion of the undercarriage leg not including the axle to support the cantilevered portion of the drive unit.

Abstract: The invention provides a method of protecting a metal substrate coated in a coating of WC—Co—Cr type by the HVOF method, the method comprising applying a lubricating agent on the coating, which lubricating agent comprises particles of solid lubricant incorporated in a fluid having surface tension that is low enough to penetrate into the pores of the coating and to entrain the solid lubricant particles therein.

Abstract: The invention relates to a method for controlling the manoeuvring of the landing gear of an aircraft, in which at least one of the steps of pulling on the doors of the bay to relieve the door retaining hook, actuating the door hook or hooks to free the doors and opening the doors is executed in response to the detection of a flight situation suitable for the occurrence of a manoeuvre order, even before the manoeuvre order is received.

Abstract: A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.

Abstract: A method of applying rotary drive by friction to an aircraft wheel that is provided with a drive track and that is mounted to rotate about an axis of rotation (X) on an axle carried by a low portion of aircraft landing gear by means of at least one friction roller (21) driven by a drive actuator (11) and associated with an actuator (23A, 23B, 30) for moving the roller between a disengaged position in which the roller is spaced apart from the drive track of the wheel and an engaged position in which the roller is kept pressed against the drive track. The method includes the step of controlling the force delivered by the actuator while they are holding the roller in the engaged position.