Abstract: Described is a modular linear actuator for use in an aerospace application, comprising: a piston housing having a closed end and an open end; a piston rod slideable within an interior of the piston housing between an extended position and a compressed position, the piston rod having a first end proximal to the closed end of the piston housing and a second end distal to the closed end of the piston housing; an attachment mechanism for removably attaching a lug end to the closed end of the piston housing, the lug end for attaching the actuator to a first component; an attachment mechanism for removably attaching a rod end to the second end of the piston rod, the rod end for attaching the piston rod to a second component; and, a piston head removably attached to the first end of the piston rod, the piston head for providing a snubbing engagement with the closed end of the piston housing.

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: A device for coupling together two elements mounted to rotate about a common axis of rotation (X) in order to enable one of the elements to be selectively driven in rotation by the other. There are two members (3, 4), one per element, the elements being axially movable relative to each other between a remote decoupled position and an engaged position in which the members provide a rotary connection between the two elements. One of the members forms a plate (3) having a face (P) perpendicular to the axis of rotation and in which a plurality of housings (15) are formed. The other one of the elements carrying rollers (23) that are mounted to rotate about radial axes to project from said element so that each of them can penetrate into any one of the housings and provide a rotary connection between the two members.

Abstract: A device for connecting a gearmotor to an aircraft wheel, the device comprising: a casing rotatably carrying a shaft that is to be driven by the gearmotor, 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 structure for selectively constraining the idle pinion in rotation with the shaft. A bushing is interposed between the shaft and the rolling bearing of the idle pinion.

Abstract: The invention relates to an aircraft wheel having a rim comprising brake discs driving keys (21), the wheel being provided with rotational driving means (210) which comprise a drive gear (211) associated with coupling members (212) of the drive gear to the rim of the wheel, the wheel being characterized in that the coupling members are fixed to the rim by fixing members (220) introduced into orifices of the rim extending at an end of the keys which are also used to hold heat shields protecting the rim.

Abstract: An aircraft wheel comprising a rim adapted to receive a tire, and a hub connected to the rim (2) in order to receive bearings for guiding the wheel in rotation about an axis of rotation (X) on an axle of the aircraft. The wheel includes at least one dog (10) that projects laterally from the rim in order to present two parallel faces (11). The dog is pierced by an orifice (12) extending from one face to the other along a generally orthoradial direction (Y).

Abstract: Method for managing the braking of a wheel (4) of an aircraft (1) fitted with a brake (11), the aircraft comprising brake control means suited to implementing an anti-skid function of the wheel (4), requiring an estimate of a rotational speed of the wheel, the aircraft further comprising means of driving the wheel including an electric motor (6) intended to drive the wheel (4) in rotation, the said electric motor (6) being fitted with a position sensor (8) intended to provide measurements of the angular position of a rotor of the motor (6). The method comprises the step, for implementing the anti-skid function, of estimating the rotational speed of the wheel (4) from measurements of the angular position of the rotor which are supplied by the position sensor (8).

Abstract: The invention relates to a tubular fusible member (21) extending along a longitudinal axis (AL) and for engaging in a two-lug clevis (14) and a single-lug clevis (12) in order to form a hinge (11). According to the invention, the fusible member (21) is constrained in rotation with one of the clevises (12, 14), and it presents a cross-section of shape that varies gradually between a central section and two distal sections, each distal section having reinforced thickness in its regions that extend parallel to the bending plane (PF) in which the fusible member (21) bends when it is stressed, the central section having a second moment of area relative to an axis normal to the bending plane (PF) that is greater than the second moment of area of the distal sections.

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: An aircraft wheel comprising two half-wheels (1, 2) assembled together by means of bolt fasteners (10; 110) clamping together disks of the half-wheels, each bolt fastener comprising a bolt (11; 111) with an end forming a screw head (12; 112) and a threaded end (13; 113) for receiving a nut (14; 114), the wheel also being fitted with drive keys (20; 120) that are fitted to one of the half-wheels for driving brake disks in rotation, the wheel being characterized in that each drive key has a first end (23; 123) that is shaped to co-operate with the screw head of one of the bolts so that said first end is held and prevented from moving when the key is in place on the wheel.

Abstract: A control box for selectively delivering orders to receivers (8, 12). The control box comprises a shaft (14) mounted to turn about an axis of rotation (X), while being capable of sliding along the axis (X) between a rest position towards which it is urged by return means (24), and an active position. An order delivery apparatus (16, 11) co-operates with the shaft (14) to deliver orders as a function of the angular position of the shaft (14). A rotary drive (15) causes the shaft to turn. A safety actuator (23) causes the shaft to slide from the rest position in which anti-rotation structure (27, 28) prevents the shaft from turning to the active position in which the anti-rotation structure (27, 28) leave the shaft free to turn under drive from the rotary drive (15).

Abstract: A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network and a DC voltage of the energy storage element, the DC voltage of the energy storage element floating relative to the DC voltage of the high-voltage electrical network and centered relative to the mass of the aircraft, the module including an input module including two filters each capable of receiving a DC voltage, a first arm and a second arm including switches, and a mechanism controlling the switches, operating per cycle of a switching period and capable of controlling at least one first switch and at least one second switch identically but offset by a half-period, whereby the first switch is open when the second switch is closed and vice versa.

Abstract: A brake for an aircraft wheel comprising an actuator-carrier 14 that carries at least one electromechanical actuator 15 having a pusher 19 that is movable along a direction parallel to an axis of rotation X of the wheel 2 and facing friction elements 7, 10 in order to apply a braking force selectively against the friction elements 7, 10. The actuator-carrier 14 and the actuator 15 include guide means 25, 32 for guiding the actuator 15 while being installed on the actuator-carrier 14 in a radial direction Y until it reaches a service position. The guide means forms a bearing surface for transmitting braking forces from the actuator to the actuator-carrier. Position-holder means 37 holds the position of the actuator in its service position and comprises a strap 37 fastened to the actuator-carrier 14 to prevent the actuator 15 from moving on the actuator-carrier 14 in the service position.

Abstract: A device for spreading a cable of carbon fibers or carbon yarns, includes a disk mounted on a rotary shaft and provided with at least one comb adapted to comb a cable of carbon fibers or carbon yarns in a direction substantially parallel to the longitudinal direction of the fibers or yarns of the cable. The comb includes a plurality of teeth protruding radially toward the outside of the disk, and a device for rotating the disk around its rotary axis. Furthermore, a method for spreading a cable of carbon fibers or carbon yarns, includes at least making the teeth of the comb of the device flush with the cable in a direction substantially parallel to the longitudinal direction of the fibers or yarns of the cable.

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: The invention relates to a device for driving rotation of an aircraft wheel comprising a rim (4) mounted to rotate on an axle (2) of landing gear about an axis of rotation (X), the device comprising a drive ring gear (103) and a drive actuator (101) having an outlet pinion (102) that co-operates with the drive ring gear to drive the wheel in rotation. The drive ring gear is mounted to rotate about the axis of the rim of the wheel, the drive device including selective coupling means (150) that are operable to link the rim and the drive ring gears together in rotation, or to disconnect them.

Abstract: The invention relates to aircraft landing gear comprising: 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 an 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. According to the invention, the unlocking actuator is of the double-acting type and the landing gear includes coupling means (31, 33) for coupling to a second end of the unlocking actuator, which means 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: 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: A protection device (1) for protecting a portion to be protected of a part, the device comprising a separable body (2) that can be separated into at least two sub-elements (4, 5), each sub-element (4, 5) having a cavity (6, 7) for receiving at least partially the portion to be protected of the part, the device having holding means (4.11, 4.12, 4.21, 4.22, 5.11, 5.12, 5.21, 5.22) for holding the sub-elements (4, 5) in position relative to one another, and at least one of the sub-elements (4, 5) having a fraction of its cavity (6, 7) that is provided with a surface (30, 31) that opposes relative sliding between the protection device (1) and the portion to be protected of the part.

Abstract: A landing gear assembly for an aircraft, the landing gear assembly including: an elongate bogie beam; a first axle bearing having an outer part rotatably coupled to an inner part, the outer part being coupled to the bogie beam, the inner part including a mounting aperture; and an elongate axle provided through the mounting aperture of the inner part and coupled thereto, wherein the axle is coupled to the inner part of the first axle bearing in a configuration such that the longitudinal axis of the axle is spaced from the axis of rotation of the inner part, such that rotation of the inner part causes a change in the orientation of the axle relative to the bogie beam.