Abstract: The invention relates to a shock-absorber for aircraft landing gear, the shock-absorber having two elements mounted to slide telescopically one in the other and defining an internal volume that is filled with hydraulic fluid and with gas, the internal volume being separated into at least two chambers by a separation including at least one throttling orifice through which the hydraulic fluid passes from one chamber to the other while the shock-absorber is being compressed. According to the invention, the separation includes at least one degassing orifice to enable gas to be transferred from one chamber to the other when the landing gear is in the deployed position, the degassing orifice being offset vertically relative to the throttling orifice so as to be located above it when the landing gear is in the deployed position.

Abstract: An aircraft landing gear, characterized in that it comprises two rocker beams carrying wheels and mounted to pivot on at least one pivot of the landing gear, the landing gear including a shock absorber device comprising two connecting rods coupled to respective ones of the rocker beams, and at least one of the connecting rods being telescopic and forming a shock absorber. The two connecting rods also are coupled to a rocking crossbar pivotally mounted on a central pivot, the pivots of the rocker beams and the central pivot of the crossbar being mounted on a leg that is connected to the fuselage of the aircraft by means of two panels that are hinged to the leg and to the structure of the aircraft about axes that are perpendicular to the hinge axes of the rocker beams and that co-operate with the leg to form a deformable parallelogram system.

Abstract: The invention relates to a method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake, the method comprising the steps of: establishing a series of direct adjustment tables for parking braking, corresponding to braking situations at different energy levels; when applying parking braking, selecting a direct adjustment table corresponding to a braking situation preceding the application of parking braking; and directly adjusting a parking braking force in application with the selected direct adjustment table.

Abstract: The invention relates to a method for the operation of a plaiting machine (1) that comprises a ring (2) carrying fiber spools (3) for plaiting layers (16, 22) of fibers (3) about a mandrel (13, 17) carried by a carrier (12) capable of movement along the axis (AX) of the ring (2), wherein after plaiting the fibers (3) are cut in order to withdraw the mandrel (13, 17), and that comprises: a hub (5, 6; 18) carried by the carrier (12) and secured to the mandrel (13; 17) while being mounted upstream therefrom; an operation for tightening the fibers (3) around the hub (5, 6; IS) with a link (11, 14) surrounding said fibers (3) after the mandrel (13, 17) has passed through the ring (2); and in which the fibers (3) are cut between the mandrel (13, 17) and the hub (5, 6; 18) before withdrawing the mandrel (13, 17).

Abstract: A circular needling table for needling a textile structure made from an annular fiber preform, the table including: a horizontal annular platen for having the annular fiber preform placed thereon; drive means for driving the fiber preform in rotation about the axis of the platen; a needling device having a needling head extending over an angular sector of the platen and driven in vertical motion relative to the platen; and guide means for guiding the fiber preform under the needling head.

Abstract: A method and apparatus are disclosed for improving densification of porous substrate using a film boiling process. In particular, the disclosed method and apparatus permit more complete densification of a substrate (i.e., densification closer to the surface of the substrate) by selectively providing a sort of barrier that reduces cooling of the surface of the substrate being densified caused by contact with the relatively cool boiling liquid precursor of the densifying material, such as carbon. In particular, contact between the substrate and the liquid precursor is reduced using one or both of physical barriers (such as a mesh material) or structures that promote the formation of an insulating gaseous layer between the substrate and the liquid precursor (such as a plate closely spaced apart from the surface of the porous substrate). The barrier is moved into operational position before the applied power level increases sharply (as is known) near the end of the film boiling densification process.

Abstract: The invention provides an aircraft wheel-and-brake set, the wheel including a rim mounted to rotate on an axle of the aircraft about an axis of rotation, and the brake including a stack of disks extending into the rim in service, and a support carrying brake actuators facing the stack of disks in order to selectively press said disks together, wherein the support carries at least one rotary drive member for driving the wheel in rotation, which drive member is carried in such a manner that it extends outside said wheel.

Abstract: A simple device for blocking and unblocking the locking member of an undercarriage having a breaker strut and including an unlocking device. The device comprises. a rotary actuator of axis parallel to the hinge axis of the links of the stabilizing member; a crank connected to a shaft of the actuator; a pawl hinged to the end of the crank and including a step; a pin secured to and at a distance from one of the links of the stabilizing member; and return means for urging the pawl towards the pin. The actuator is actuatable between a first angular position in which the pin is in contact with the pawl facing the step while the links are substantially in alignment, and a second angular position that the crank reaches when the step of the pawl has pushed back the pin, taking the links of the stabilizer member out of alignment.

Abstract: A locking device for locking together first and second elements that are movable relative to each other in an axial direction. The device has a bushing secured to a first element and catches that are cantilevered-out in an axial direction and are elastically deformable. The device also has an anchor portion secured to a second element and an annular setback to receive hook-shaped ends of the catches. The device also has a locking sleeve mounted to move relative to the catches between a release position in which the catches are free to flex, and a blocking position in which the catches are prevented from flexing, wherein the locking sleeve is movable in rotation relative to the catches and includes a circumferential succession of gaps and of obstacles.

Abstract: The invention relates to a method for manufacturing a mechanical member in composite material, such as a connecting rod (19), comprising successive operations of applying layers of reinforcing fibres braided all about a mandrel, comprising, between two operations of applying layers of braided reinforcing fibres, a step: of placing at least one element formed of pultruded reinforcing fibres (14?), oriented longitudinally (AX); and of at least temporary attachment of each pultruded element (14?) to the last layer of braided reinforcing fibres, and in which a resin is then injected into the various braided layers before this resin is polymerized in order to form a rough connecting rod.

Abstract: The invention relates to a bar for an aircraft wheel, the bar comprising an oblong body (2) extended at each end by respective endpieces (4, 5) extending parallel to the body and parallel to each other, the endpieces being offset relative to each other. The invention also relates to a wheel specially adapted to receive such a bar.

Abstract: The invention relates to a method for manufacturing an arm (16) in composite material, this arm comprising a main body incorporating a bearing (22) designed to receive a shaft passing through it transversely, this method comprising the steps of: manufacturing a hub (11) by winding reinforcing fibres around a generally tubular support (12); manufacturing at least one sleeve (14); attaching the hub (11) to one end of the sleeve (14) and transversely to the sleeve (14) in order to form a mandrel; applying one or more layers of braided reinforcing fibres (21) around this mandrel with a machine for braiding reinforcing fibres (19); injecting and polymerizing resin into the layer or layers of braided fibres (21). The invention applies notably to an arm forming an undercarriage rocker arm of an aircraft.

Abstract: A device for connecting a gear motor to an aircraft wheel, the device comprising: a casing rotatably carrying a shaft that is to be driven by the gear motor, and on which a pinion is mounted idle by means of a rolling bearing; a toothed ring for being constrained in rotation with the aircraft wheel and arranged to mesh permanently with the idle pinion; and rotation securing means for selectively constraining the idle pinion in rotation with the shaft. With this structure, a smooth bearing is interposed between the shaft and the rolling bearing of the idle pinion.

Abstract: The present invention relates to an electromechanical actuator comprising an electric motor (11) for driving an output shaft (4) in rotation via a reduction gear (20) and passive regulation means (30) allowing for control of the speed of rotation of the output shaft, and comprising a braking member (30), arranged between an output of the reduction gear and the output shaft to be driven, said braking member being arranged to ensure two different braking levels depending on the direction of rotation of the shaft, characterized in that the braking member is of hydraulic type and comprises fluid decantation means (33) between two chambers (34, 35) decanting under the effect of the rotation of the output shaft through a selective drawing member (41) which, depending on the direction of rotation of the actuator, opposes two distinct resistances to the decantation of the fluid from one chamber to the other.

Abstract: A method for producing a metallic part including inner reinforcements of ceramic fibers, according to which: at least one recess for an insert is machined in a metallic body having an upper surface; at least one insert of ceramic fibers in a metallic matrix is arranged in the recess; the insert is covered with a cover; the gap around the insert is placed under a vacuum and hermetically sealed; the entire metallic body with the cover is treated by hot isostatic compaction; and the treated assembly is machined to produce the part. The insert is rectilinear, and the recess for the insert in the metallic body forms a rectilinear groove, the cover being dimensioned so as to be able to placed on the insert in the recess after having been shrunk by cooling and to establish a tight fit in the groove by dilation such as to close the space.

Abstract: The invention relates to a device for manoeuvring, on the ground, a door of an aircraft landing gear, the door being linked with door manoeuvring means and uplock means for locking the door when it reaches the closed position, at least one unlocking electromechanical actuator arranged to act upon the uplock means with a view to deactivating them during opening of the door in flight. According to the invention, the device comprises control means 17 which can be operated by an operator on the ground in order to control at least: an opening sequence during which the unlocking electromechanical actuator is actuated in order to deactivate the uplock means, a closing sequence during which the manoeuvring means are actuated in order to close the door again.

Abstract: The invention provides a method of taxiing an aircraft having at least one nose undercarriage at the front of the aircraft and main undercarriages, each undercarriage having wheels, the method comprising the steps of: fitting at least one of the wheels carried by the nose undercarriage with a main taxiing motor member, and fitting at least one of the wheels carried by the main undercarriages with an auxiliary taxiing motor member; and in response to a taxiing order, powering the main taxiing motor member to cause the aircraft to taxi, and in particular if the driving force developed by the main taxiing motor member on the aircraft is insufficient, powering the auxiliary taxiing motor member, as required.

Abstract: An aircraft undercarriage comprising two rocker beams (1, 2) carrying wheels and mounted to pivot on a common pivot (Y1), the undercarriage including a shock-absorber device comprising two connecting rods (5, 6), each coupled to a respective one of the rocker beams, at least one of the connecting rods being telescopic and forming a shock absorber, the two connecting rods also being coupled to a rocker (7) pivotally mounted on a central pivot (8). The common pivot of the rocker beams is secured to the structure of the aircraft and is mounted in a fixed position thereon, while the central pivot of the rocker is movable between a first position in which the rocker beams are in a landing position, and a second position in which the rocker has pulled on the connecting rods to cause the rocker beams to pivot towards a retracted position.

Abstract: The invention relates to a method for making an arm for a hinged structure such as an aircraft landing gear structure, this arm comprising a main body (30; 130; 230) extending in a longitudinal direction (AP; BP; CP), and including an interface (13; 113; 213) such as a yoke radially protruding from the main body, this method including the steps of: making an insert (11; 211) including a base (12; 212) carrying the interface; making a mandrel (10; 110) integrating the base of the insert so that a portion of the external surface of this mandrel is delimited by a portion of the external face (17; 217) of the base of the insert; applying one or more layers of reinforcing fibers (31; 131; 231) around the mandrel and over all its length, so that each layer has the interface (13; 113; 213) passing through it without covering the interface; injecting resin into the layer or layers of reinforcing fibers (31; 131; 231) and at the level of the area of contact (32) of these layers (31) with the external face (17; 217)

Abstract: The invention relates to a method of feeding energy to actuators associated with the undercarriages forming the landing gear of an aircraft, the aircraft comprising: a main power supply that operates independently of rotation of wheels carried by the landing gear; and a local power supply comprising one or more local generators, each driven by rotation of a wheel carried by an undercarriage; the method of the invention comprising the following steps: in a nominal mode of operation, powering said actuators by the local power supply; and in an additional mode of operation, when the delivery of energy by the local power supply is not sufficient, providing additional energy or all of the energy required by said actuators by means of the main power supply.