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: A method of managing a steering command for a steerable portion 3 of nose landing gear 2 of an aircraft 1. The method implements servo-control to servo-control of a steering actuator 6 to an angle position setpoint ?set for the steerable portion 3. The servo-control includes calculating an error ? by subtracting a reference angle ?est from the angle position setpoint ?set. The reference angle ?est is an angle determined by calculation as a function of a longitudinal speed Vlong and a yaw rate ? of the aircraft 1.

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: A landing gear (10), including: a bogie beam (12); an axle (14) pivotally connected to the bogie beam (12); a locking member (40) coupled to the axle (14) such that movement of the axle (14) invokes movement of the locking member (40), said movement of the locking member (40) defining a swept volume; and a locking mechanism (60) coupled to the bogie beam (12) and including first (65a) and second glide members, (65a, 65b) the locking mechanism (60) being arranged to move the glide members (65a, 65b) between locking positions, where glide members (65a, 65b) are within the swept volume on opposing sides of the locking member (40) and in which position the locking mechanism (60) is arranged to lock the locking member (40) in a predetermined position, and non-locking positions, where the locking mechanism (60) is arranged permit movement of the locking member (40).

Abstract: The invention relates to a method for locking a mobile element (101) of an aircraft, such as a hold door or a landing gear, the mobile element being moved between a deployed position and a closed or retracted position by means of an actuator (200) having a sliding stem (3) coupled to the mobile element, the stem being mounted so as to be able to slide in a body (1) of the actuator between an extended position corresponding to the deployed position of the mobile element and a withdrawn position corresponding to the closed or retracted position of the mobile element. The method of the invention comprises the step of positively blocking the sliding stem of the actuator in the withdrawn position.

Abstract: A hydraulic actuator containing a hollow body defining a cylindrical cavity and a rod which is mounted to slide within the body along a sliding axis between two end positions and which is integral with a piston sliding in a sealed manner within the cylindrical cavity in order to define two chambers. The rod defines an interior passage, connecting the two chambers, which has a valve comprising a shut-off member which is returned towards a seat and closes the passage. The rod receives a push member which can move relative to the rod between a position apart from the shut-off member and a position forcing the shut-off member to open. The push member is constrained, when the rod reaches the end of its stroke, by the push member engaging with a portion of the hollow body.

Abstract: A brake actuator comprising a sleeve (1), a piston (3) sealingly slidably mounted in the sleeve to apply a braking force, the piston being provided with an internal cage (21), and a wear compensating device (10) which defines a retracted position of the piston in the sleeve by means of an axially mobile stop which is able to be moved forward by the piston during the application of a braking force and/in frictional relationship with a fixed part (12) of the wear compensating device attached to the sleeve. The mobile stop comprises a radially deformable bushing (16) which cooperates with an olive (15) which is attached to a distal end of the fixed part of the wear compensating device. The bushing comprises means for guiding its proximal end (17) against an internal face of the internal cage (21).

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 provides an emergency power network for aircraft, for powering actuator motors (4) connected to the network, the network comprising a power bus (11) adapted to convey three-phase AC power generated by at least one DC/AC converter (12) that is powered by a DC source of the aircraft, the converter being fitted with modulator means for modulating the voltage and/or the frequency of the three-phase power generated thereby.

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: The invention relates to an electromechanical brake actuator for an aircraft wheel, comprising an electric motor (2) with a stator (3) and a rotor (4), a screw/nut assembly, of which one of the elements is rotationally driven by the motor and the other of the elements is compelled to slide without rotation to selectively exert a force on a stack of discs, the actuator comprising a park blocking member (10) suitable for selectively blocking the rotor of the motor at least when the sliding element exerts a force on the stack of discs. The park blocking member comprises a shuttle (17) that can move between a stable position of blocking of the rotor of the motor and a stable position of freeing the latter under the action of a pulse actuator (22, 24, 25) switching the shuttle from one position to the other, the brake actuator comprising means (9, 18) for forcing the shuttle to the freeing position when the motor of the brake actuator is powered.

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: The invention provides a control box for selectively delivering orders to receivers (8, 12), the control box comprising: a shaft (14) mounted to turn about an axis of rotation (X), while being capable of sliding along said axis (X) between a rest position towards which it is urged by return means (24), and an active position; order delivery means (16, 11) co-operating with the shaft (14) to deliver orders as a function of the angular position of the shaft (14); rotary drive means (15) for causing the shaft to turn; and safety actuation means (23) for causing the shaft to slide from the rest position in which anti-rotation means (27, 28) prevent the shaft from turning to the active position in which the anti-rotation means (27, 28) leave the shaft free to turn under drive from the rotary drive means (15).

Abstract: The invention relates to a management method for managing a turning movement of an aircraft taxiing on the ground, the aircraft having wheels each fitted with an independent drive device, in which method commands are generated for the independent drive devices so that at least some of those devices contribute to the turning movement. According to the invention, the method comprises the steps of: estimating at each instant during the turning movement: an instantaneous total power developed by all of the independent drive devices in response to the commands; and an instantaneous mean angular acceleration for all of the wheels; and adapting the commands to the independent drive devices such that the total instantaneous power developed by all of the independent drive devices is minimized, while conserving the mean angular acceleration.

Abstract: A method of manufacturing a mechanical component, and winding device to implementing the method. The component includes at least one insert of metal matrix composite, within which matrix ceramic fibers extend, the composite insert obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath. The method manufactures an insert preform by winding a bonded lap or bundle of coated filaments about a cylindrical component. At least some of the winding is performed in at least one rectilinear direction. The method further inserts the insert preform in a first container; performs hot isostatic compaction of the first container; and machines the first container to form a rectilinear insert.

Abstract: A method of managing the braking of an aircraft, the aircraft having a plurality of wheels R1, . . . , R12, each fitted with a brake F1, . . . , F12 adapted to generate a braking force in response to brake pedals 5 being depressed. The management method comprising the steps of: distributing the wheels fitted with respective brakes in at least two distinct groups G1, G2, G3, G?1, G?2, G?3; allocating respective relationships to each of the groups of wheels for determining how braking force varies as a function of the depression of the brake pedals; and modifying the distribution of the wheels in response to a predetermined event occurring.

Abstract: The invention relates to fiber reinforcement for making an elongate mechanical part (10) out of composite material having a lug (14) at at least one end for receiving a pin for making a pivot connection with another part, the fiber reinforcement being made from a central fiber structure (106; 106?) for forming a core that is obtained by three-dimensional weaving, from a peripheral fiber structure (16; 16?) that is to form a belt surrounding the central structure so as to form at least one empty cylindrical space in the lug of the part, and from at least one annular fiber structure (112; 112?; 112?) that is to form a ring that is formed inside the empty space provided between the central structure and the peripheral structure.

Abstract: An electric brake for an aircraft wheel comprising a support 4 formed by a torsion tube 5 and by an actuator-carrier 6, a stack 7 of disks mounted around the torsion tube 5, electromechanical actuators 8 carried by the actuator-carrier 6, each actuator comprising an electric motor 12 and a pusher 14, the electric motor 12 being adapted to move the pusher 14 facing the stack 7 of disks in order to apply a braking force selectively to the stack 7 of disks; and temperature measurement means for measuring a temperature representative of a temperature that exists in the stack 7 of disks. The temperature measurement means comprises at least one temperature sensor 18 arranged in the pusher 14 of one of the electromechanical actuators 8 so as to be located in the immediate proximity of the stack 7 of disks when the pusher 14 is brought into contact therewith.

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: The invention relates to a method of using and renovating a disk (9) from a stack of disks (7) of a vehicle brake, the method comprising the steps of using the disk during a plurality of lives and of compensating for loss of thickness after each life by assembling the disk with a complementary portion.