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: An auxiliary mechanism includes a lever unit, a spring unit and a positioning unit. One of the units pivotally connects to the upper portion of a main shock absorber strut so as to pivot between a predetermined lower position for take-off and landing and an upper position. Another unit pivotally connects at an upper end to the upper portion of the main shock absorber strut and pivotally connects at a lower end to the first unit. A third unit pivotally connects at a lower end to the bogie beam at an auxiliary pivot and connects at an upper end to the lever. The positioning unit assumes either a contracted state or extended state for taxiing, take-off and landing, and assumes the other state for stowing the landing gear after take-off. The spring unit provides spring resistance to pivotal movements of the bogie beam about the main pivot during taxiing.

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.

Abstract: The invention relates to a method of managing a steering control for a steerable portion of an aircraft undercarriage, the method comprising implementing servo-control to servo-control an electromechanical steering actuator on an angular position setpoint, wherein, according to the invention, the servo-control implements a control relationship H? type, the position and speed information being delivered by means of a fieldbus of deterministic type to a computer that implements the servo-control.

Abstract: A semi-levered landing gear for an aircraft includes a main shock absorber strut, a bogie beam and an auxiliary actuator mechanism. The bogie beam extends fore and aft of an airframe of the aircraft with forward and aft axles for respective forward and aft wheels, and a main pivot between the forward and aft axle pivotally connected to the lower portion of the main shock absorber strut. The auxiliary actuator mechanism includes a spring unit pivotally connected at a lower end to an auxiliary pivot on the bogie forward of the main pivot, and at an upper end to an anchor point offset from the pivot connection of the upper portion to the aircraft fuselage. During stowing the strut and spring unit pivot together about different pivot points, causing a relative longitudinal movement between the main pivot and auxiliary pivot that further tilts the bogie beam to a stowing position.

Abstract: A circular needling machine for needling a textile structure formed from a helical fiber sheet, includes a needling table disposed beneath a feed table for feeding a helical fiber sheet for needling. The feed table includes a circular belt conveyor for receiving thereon a helical fiber sheet for needling, the conveyor being centered on a vertical axis and having a radial slot opening out under the circular conveyor to unwind continuously the fiber sheet received on the conveyor, the slot opening out under the conveyor towards a substantially straight chute that extends vertically between the conveyor and a support tray of the needling table centered on the vertical axis of the conveyor so as to take up the sheet unwound from the conveyor and bring it onto the needling table, the support tray having means for driving the fiber sheet in rotation about the vertical axis.

Abstract: An auxiliary actuator mechanism includes a lever, a spring unit and a control linkage. The lever is pivotally connected to the upper portion of a main shock absorber strut, and pivotable between an upper position for take-off, and a lower position. The spring unit is pivotally connected at an upper end to the lever and at a lower end to the bogie at an auxiliary pivot forward of the main pivot. The control linkage is connected between the lever and the upper portion of the main shock absorber strut to define the upper predetermined position of the lever. The control linkage is connectable to an anchor point that moves relative to the upper portion of the main shock absorber strut during stowing, and is operated by initial stowing movement of the stowing mechanism to lower the lever from the upper position to a stowing position.

Abstract: A device for selectively connecting a tire to a pneumatic unit of an aircraft, the tire forming part of a wheel mounted to rotate on a hollow axle of the aircraft, the device comprising a stator and a rotor that is mounted to rotate relative to the stator and that includes a structure enabling it to be rotated by the wheel. The stator is bell-shaped and is designed to be received as a push-fit in the axle, and includes an end wall carrying a first pneumatic port for connection to the pneumatic unit via a tube running along the inside of the axle, the rotor extending substantially inside the stator.

Abstract: The invention relates to a braking system architecture for an aircraft fitted with electromechanical brakes including at least one electromechanical actuator. In accordance with the invention, the architecture comprises at least one proximity unit disposed in the proximity of the brakes at the bottom of the undercarriage and including input/output means for collecting and calibrating at least signals coming from sensors associated with the brakes, and for transmitting the signals as processed in this way to control members for controlling the actuators by means of a communications bus running along the undercarriage, the proximity unit further including control means for controlling the blocking members of the actuators.

Abstract: The invention relates to an aircraft landing gear of deformable-parallelogram type, including: a leg including a casing (1) having a lower end on which a rocker arm (3) carrying at least one wheel is hinged by means of a pivot (2), a shock absorber (5) being connected between the rocker arm and the casing; two panels (10, 11) each hinged on the one hand on the structure of the aircraft and on the other hand on the leg, about parallel axes; According to the invention, one of the panels (11) is hinged on the leg whilst being connected to the casing by a pin on one end of the pivot (2) of the rocker arm.

Abstract: There is described a landing gear having a bogie including a elongated beam (2) for accommodating at least two axles receiving each a pair of ground engaging wheels, at least one axle (5) being pivotally mounted on the elongated beam. The landing gear further includes axle travel limitation means (10) extending between said pivotable axle and said elongated beam to be hitched up thereto, said travel limitation means being deformable one way starting from an stable and lockable state thereof corresponding to a landing position of said pivotable axle. There are also described independently lockable and actuatable telescopic struts.

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

Abstract: A method of manufacturing an elongate insert configured to be integrated by CIC in a metal container, including coated yarns bonded together, the coated yarns being formed from metal-coated ceramic fibers. The method includes placing the coated yarns side by side in a bundle and pulling the fiber bundle through a shaping element so as to compact the fiber bundle transversely while forming the fiber bundle so as to have a defined cross section. A metal part incorporating a fibrous insert can be manufactured by the CIC technique.

Abstract: A braking system for an aircraft with electric brakes comprising plural electromechanical actuators (2). The system comprises a braking control unit (20) delivering a normal braking setpoint (21) for one or more controllers (10) of the actuators, and selection means (15) for causing the braking system to operate in a plurality of modes. The system includes: a normal braking mode where the control unit generates a normal braking setpoint (21) for the controller(s); an ultimate braking mode, having priority over the normal braking mode, being responsive to a parking control member, and controlling actuators to respond to the actuation of the parking control member; and a parking braking mode, applied in response to the parking control member and only if the aircraft is stationary, in which the actuators are controlled to apply a force in response to the parking control member being actuated and are then blocked in position.

Abstract: The invention relates to a method of controlling the steering of a steerable portion of an aircraft undercarriage that is fitted both with a steering member for steering the steerable portion and also with at least two angular position sensors for sensing the angular position of the steerable portion in order to deliver respective signals representative of the angular position of the steerable portion, wherein the steering member is controlled by means of servo-control using information that is representative of the angular position of the steerable portion. According to the invention, the information representative of the angular position that is used is a mean of the angular positions sensed by the at least two angular position sensors.

Abstract: A method of protecting an aircraft undercarriage (1) while it is being towed by means of a tow bar (13) hitched to a steerable bottom portion of the undercarriage, the method including the step of generating an alarm when a towing force imposed by the tow bar on the undercarriage reaches or exceeds a predetermined force threshold. The threshold is caused to vary as a function of an orientation of the steerable bottom portion of the undercarriage.

Abstract: Aircraft landing gear including an axle pivotally connected to a bogie beam and a locking device. The locking couples the axle to the bogie beam, and has a movable member and a follower. The movable member is movable between first and second configurations. Movement of the movable member towards the second configuration causes corresponding movement of the follower so as to transfer a steering force to the axle through the follower which causes the axle to rotate in a first direction. With the movable member in the first configuration, the follower is in a first configuration that inhibits the movable member being moved by an external force applied to the axle. With the movable member in the second configuration, the follower in a second configuration that permits the movable member to be moved by an external force applied to the axle.

Abstract: The invention relates to a method for making a connecting rod (6) made of a composite material and including a yoke (7) for receiving a mechanical axis, said yoke (7) including two parallel arms (7a, 7b) perpendicular to the mechanical axis, wherein the method comprises the steps of: making a mandrel (11) defining a single piece sufficiently rigid for receiving fiber layers (8a-8e, 9a-9d); applying onto said mandrel (11) base fiber layers (8a-8e) and additional layers (9a-9d) interleaved between the base layers (8a-8e) at the yoke (7, 7a, 7b) in order to form an additional thickness thereon; inserting lugs (13a, 13b) extending through the intermediate layers (9a-9d) and the base layers (8a-8e); injecting resin into the base layers (8a-8e) and the intermediate layers (9a-9d) and polymerizing said resin.

Abstract: The invention relates to a device (32) for rotationally coupling a wheel (10) with a ring (31) for driving the wheel (10) mounted so as to rotate coaxially with the wheel (10). According to the invention the device (32) comprises a plurality of connecting members (60) each extending in a direction contained in a plane perpendicular to the axis of rotation and forming an angle with a radial direction, the connecting members (60) being pivotably mounted on the one hand on the wheel (10) and on the other hand on the ring (31).