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: A method of manufacturing a mechanical component, a mechanical component thus obtained, and a winding device designed for implementing the method of manufacture. The mechanical component includes at least one insert made of metal matrix composite, within which matrix ceramic fibers extend, the composite insert being obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath, the method including manufacturing at least one insert by winding a bonded lap or bundle of coated filaments about a component of revolution. At least some of the winding is performed in a rectilinear direction.

Abstract: The invention relates to a brake for an aircraft wheel comprising firstly calipers with an outer jaw (103) receiving a stationary brake pad (108) and an inner jaw that is movable under drive from the braking actuator (105) and that receives a movable brake pad (107), and secondly a disk (109) that extends between the brake pads and that includes means (110) for constraining it to move in rotation with the wheel; at least one of the brake pads includes a protrusion (120) projecting from a rear face of the pad to be received in a matching receptacle (123) of the associated jaw and serving both to position the pad on the jaw and to transmit braking forces from the stationary pad to the associated jaw.

Abstract: The invention provides a steering resetting method for an aircraft undercarriage that includes a leg in which a steerable bottom portion is mounted to slide against a suspension force generated by a shock absorber, the undercarriage being provided with a controllable steering member for causing the steerable bottom portion to swivel in response to an angular position setpoint, the undercarriage also including at least one angular position sensor adapted to generate an electrical signal representative of the angular position of the steerable bottom portion and suitable for use in controlling the steering member; the method comprises the step, performed when the steerable bottom portion is in an indexed angular position while the aircraft is in flight and the undercarriage is fully extended, of setting the electrical signal from the sensor to a determined reset value.

Abstract: 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. The method includes correcting the braking setpoint as a function of the pitch angle ? of the aircraft 1 during braking.

Abstract: A method of measuring the thickness of a coating layer of a workpiece, the layer being formed on a substrate of the workpiece. The method comprises several steps. First, feeding a probe alternating electrical signal to induction device in order to induce a magnetic field in the workpiece. Second, measuring at least one physical characteristic that varies as a function of the magnetic field induced in the workpiece. Third, determining first and second values of an indicator, the values being determined respectively from measurements of the physical characteristic taken when the electrical signal has first and second given frequencies. Forth, calculating the difference between the first and second values of the indicator and determining the thickness of the coating layer as a function of the difference and of predetermined data correlating: the difference between the values of the indicator; and corresponding values for thicknesses of the coating layer.

Abstract: A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part.

Abstract: After making a carbon fiber preform and prior to completing densification of the preform with a carbon matrix, impregnation is performed with a liquid formed of a sol-gel type solution and/or a colloidal suspension enabling one or more zirconium compounds to be dispersed. The impregnation and the subsequent treatment, up to obtaining the final part, are performed in such a manner as to have, in the final part, grains or crystallites of one or more zirconium compounds presenting a fraction by weight lying in the range 1% to 10% and of composition having at least a majority of the ZrOxCy type with 1?x?2 and 0?y?1.

Abstract: The invention relates to an electrohydraulic actuator comprising a body (1) that defines a cylindrical cavity (2) in which a piston (3) slides in leaktight manner and divides an inside volume of the cavity into two chambers (A, B) of variable volume, the piston being associated with at least one rod (4) passing in leaktight manner through an end wall of the cavity, the actuator including a bidirectional pump (5) having two ports (P1, P2), each connected to one of the chambers, an electric motor (8) for selectively driving the pump in one direction or the other, the pump being placed inside the piston of the actuator so as to move together therewith.

Abstract: A method of fabricating a mechanical member for aircraft, including a plurality of operations of braiding and depositing layers of braided reinforcing fibers on a mandrel (11) by using braiding machine. Each operation comprises braiding a braided layer and depositing it by moving the mandrel (11) along a central axis of the braiding machine. Each of the various superposed braided layers comprises both longitudinal fibers (12, 12G) that are parallel to a main direction of the mandrel (11), and interlacing fibers that are inclined. At least one operation is configured to form and deposit a braided layer having, in at least one cross-section of the member, a density of longitudinal fibers that differs depending on whether consideration is given to one angular region (S1) or another angular region (S2) of the same extent around the center of gravity (G) of the mandrel (11) in the section under consideration.

Abstract: A method of managing the lifetime of a stack of disks of an aircraft brake having at least one braking actuator including a pusher adapted to press selectively against the stack of disks in order to generate a braking force for an associated wheel, the method comprising the following steps, for a given flight of the aircraft: actuating the actuator to cause the pusher to come into contact with the stack of disks; deducing therefrom a stroke of the actuator, and by taking the difference with a nominal stroke stored in memory corresponding to the stack of disks when new, deducing a current level of wear (U) for the stack of disks; from the current level of wear and from the number of flights (N) flown since the new stack of disks was mounted, using an extrapolation method to estimate a potential number of flights (?N) before the stack of disks reaches a maximum acceptable level of wear (Umax).

Abstract: The invention relates to a heat treatment oven comprising a loading or treatment zone, at least one gas inlet, a gas preheater chamber situated in the oven between the gas inlet and the loading or treatment zone, a susceptor comprising at least a side wall surrounding the preheater chamber and the loading or treatment zone, and a field winding suitable for heating the side wall by induction. The portion of the side wall of the susceptor that is situated around the preheater chamber presents at least two recesses spaced apart circumferentially from one another so as to form portions of reduced thickness in said portion of the side wall.

Abstract: The invention relates to an electromechanical brake, in particular for aircraft, the brake comprising a support carrying at least one electromechanical actuator comprising a pusher that is axially displaceable towards friction elements in order to apply a braking force to the friction elements, selectively, wherein the actuator is mounted on the support via a connection member allowing at least a portion of the actuator carrying the pusher to tilt angularly.

Abstract: A method of fabricating an aircraft landing gear rocker beam comprising a body having a clevis (24) with two lugs (19, 21) parallel to a direction that is radial relative to the body, the method comprising the steps of: forming a first mandrel; applying one or more first braided fiber layers (11) on the first mandrel; fitting a second mandrel element on the assembly as constituted in this way, the second mandrel element extending between the two lugs (19, 21) of the clevis (24) that is to be formed; applying one or more second braided fiber layers (17) on the assembly as constituted in this way; injecting resin into the various layers (11, 17) and polymerizing the resin; and machining the resulting workpiece blank in order to cut away a region of the second braided layers (17) in order to separate the two lugs (19, 21) of the clevis (24) from each other.

Abstract: A braking actuator for a brake of an aircraft, the actuator comprising: an electric motor; a pusher actuated by the motor; and a position sensor for sensing the position of the movable portion of the motor and provided with transmitter and receiver members. The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.

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 multifunction device for an undercarriage, the device comprising 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, a telescopic second shaft rotatably mounted in the undercarriage and extending down along the undercarriage to the proximity of wheels carried thereby, and motor means adapted to cause the first shaft to rotate. The telescopic second shaft is a single shaft and it extends inside the undercarriage to the proximity of an axle carrying the wheels of the undercarriage, being connected to a differential connected to the wheels via drive shafts extending inside the axle.

Abstract: The invention relates to a device for selectively transmitting force, the device comprising a first element and a second element that is movably mounted on the first element, a friction member being arranged between the first element and the second element to exert a friction force between them, which force presents a maximum value that depends on prestress imparted by a presser member. The device includes control means for varying the prestress imparted by the presser member to the friction member and arranged, where appropriate, to substantially release the prestress imparted by the presser member so that the prestress becomes substantially zero.

Abstract: 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. The method comprises the steps of (1) monitoring the pressures of the tires carried by the wheels, and in response to detecting at least one of the following events: (1A) the pressure of one of the tires is less than a first predetermined threshold, and ( 1B) the difference between the pressures of two of the tires is greater than a second determined threshold; (2) activating the steering control, if the steering control is not activated; and (3) implementing a steering control relationship that is modified compared with a nominal control relationship used when the tires are properly inflated.

Abstract: The invention relates to landing gear mounted on an aircraft in such a way as to be movable between a stowed position and a deployed position, the landing gear incorporating: a barrel mounted in a hinged way on the aircraft; a folding strut with two arms; a stabilizing member to stabilize the strut in an aligned position, having two rods hinged to each other; a telescopic unlocking member having one end coupled to one of the rods, the telescopic member being selectively activatable to break an alignment of the rods. According to the invention, said rod has an aperture in which the end of the telescopic unlocking member engages and which is arranged in such a way that, when the telescopic member is activated, said end interacts with an end of the aperture to move the associated rod toward a non-aligned position which said rod reaches when the telescopic member reaches an internal stop, the aperture allowing any hinged movement of the rod beyond the non-aligned position.