Abstract: An anti-lofting deflector for landing gear having two wheels on an axle, the deflector comprising: a stationary support (5) for being fastened in service to a portion of the landing gear that carries the axle in order to extend between the wheels and present a distal end behind the wheels; a first flap (2) hinged to the support via its distal end about a first hinge axis (X1) substantially parallel to the axle; a second flap (3) hinged to the first flap about a second hinge axis (X2) substantially parallel to the first hinge axis; and a return member (11) arranged so as to urge the second flap against an abutment of the first flap that prevents the second flap from becoming aligned with the first flap, and to urge the first flap against an abutment of the stationary support that prevents the first flap from folding against the support.

Abstract: A method of actuating undercarriage latching boxes and associated hatch latching boxes of an aircraft in an emergency mode, the latching boxes having at least one feed port and at least one unlatching member that is operable when the port is fed with fluid under pressure, the aircraft also being provided with a hydraulic braking circuit. The method includes connecting at least one tapping circuit to the braking circuit of the aircraft in association with an isolation valve that is kept, in a normal mode, in an isolation state and that can be controlled to be placed in an open state in which at least some of the feed ports of the latching boxes are fed by the tapping circuit connected to the braking circuit.

Abstract: A method of fabricating a connecting rod (6) out of composite material using three-dimensional fabric of woven reinforcing fibers, the connecting rod (6) extending in a main direction. The method comprises the steps of: cutting out one or more base pieces (7, 8) from a three-dimensional fabric; cutting out one or more reinforcing pieces (9, 10) from a three-dimensional fabric; installing the various pieces (7, 8, 9, 10) on a support in order to shape them; securing the various pieces (7, 8, 9, 10) to one another by stitching (12, 13, 14, 15) using reinforcing fibers in order to constitute a reinforcing fiber preform; installing the preform on a mandrel; and injecting resin into the preform and polymerizing the resin.

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 while being connected to the casing by a pin on one end of the pivot (2) of the rocker arm.

Abstract: The invention relates to a method of limiting a current idc supplied by a DC power supply, the method comprising: interposing a switching stage between the power supply and a load, the switching stage including a controllable switch in series with a freewheel diode; and periodically controlling the switch so that for each period of duration T, the following averaged quantity 1 T ? ? o t ? i _ · ? t is calculated in which i is a current that is an image of the power supply current idc, the averaged quantity being reset to zero at the beginning of each period, with the switch being caused to be closed so long as said averaged quantity remains below a predetermined current threshold ithresh, and with the switch being caused to be open, otherwise.

Abstract: A process for manufacturing a structural part made of an organic matrix composite including: production of a fibrous structure, forming a preform by braiding rovings of a fibrous material on a mandrel that includes a reinforcement in its axial extension, impregnation of the preform with an organic resin; and curing of this resin, the reinforcement, forming the cover, having a bore with an axis perpendicular to the axis for housing a connecting member. Barbs, some of which are projecting, are incorporated into the reinforcement over at least part of the surface of which lying on either side of the bore, the braiding being carried out around the barbs so that the rovings at least partly criss-cross around the barbs.

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: The invention relates to a telescopic actuator comprising a body (1) defining a cylindrical cavity of longitudinal axis (X); a rod (3) mounted to slide telescopically in the cylinder along the said axis; a nut (7) secured to the rod; a lead screw (4) mounted on the cylinder to extend along and rotate about the said axis (X) and collaborate with the nut in such a way that a rotation of the lead screw causes a telescopic movement of the rod in the cylinder; means (8, 9, 10) for driving the rotation of the lead screw. According to the invention, the nut is mounted on the rod to be axially retained thereon by retaining means (12, 13, 14; 30 to 38) which can be made to release the nut axially from the rod.

Abstract: A telescopic actuator comprising a cylinder having a structure for coupling the cylinder to a first external element a rod mounted to slide telescopically in the cylinder along a sliding axis and including a structure for coupling it to a second external element and a lead screw mounted to rotate in the cylinder about the sliding axis and extending inside the rod to co-operate with a nut secured to the rod, such that rotating the lead screw causes the rod to slide. There also is a drive structure for driving the lead screw in rotation and a retention structure for axially retaining the lead screw. The retention structure holds a bearing of the lead screw captive in an axial direction and is arranged to retain the bearing of the lead screw with axial clearance suitable for absorbing movements imparted to the rod relative to the cylinder.

Abstract: A device for coupling an actuator for operating an aircraft undercarriage to an aircraft structure. The device comprises a lever having a first end for hinging to the structure of the aircraft, and a second end to which the actuator is hinged, a pre-loading structure acting on the lever to urge it towards a stable rest position that is occupied by the lever in the absence of any force transiting through the actuator; and an abutment structure defining at least one working position for the lever when the actuator is activated.

Abstract: A mechanical transmission device for transmitting a threshold force, comprising first and second elements rotatably mounted relative to each other about an axis of rotation, and having a transmitter member interposed between them to constrain the two elements to rotate together when a torque is imparted to one up to a threshold torque beyond which the two elements become movable in rotation. The transmitter member has a first friction disk constrained to rotate with the first element, and a second friction disk facing the first disk. It also has a bearing member that is axially movable to press the disks together and against a bearing turntable of the first element under drive from a presser member. Finally, it has a rotary drive, interposed between the bearing member and the second element, which are arranged to cause the bearing member to move axially against the presser member during rotation.

Abstract: In the field of aviation, a method of fabricating a composite-material rod. The method comprises a first step of fabricating a mandrel comprising a sleeve of composite material and solid inserts of composite material secured to the ends of said sleeve to constitute a rigid whole. Then, one or more layers of braided fibers are applied around the mandrel by using a fiber-braiding machine. Next, a resin is injected into the layers of braided fibers so as to establish cohesion rigidly bonding the braided fiber layers and at least the ends of the mandrel in order to form a rod body out of composite material having reinforced ends. Finally, respective holes are drilled at each end of the rod body, each hole passing through the layers of braided fibers and also through the corresponding insert.

Abstract: During implementing a composite metal part by compaction of an insert having reinforcing fibers in a metal body or container, gas used for compaction may enter the cavity formed in the container for receiving the insert between a lid covering the insert and the container, which can prevent or degrade compaction and diffusion welding of fiber sheaths of the insert therebetween and/or with walls of the cavity. To solve this problem, the present method includes initiating isostatic compaction by a phase including raising and maintaining temperature, followed by a phase including hot-feeding pressurized gas, and machining an assembly to obtain the part. The temperature raising phase includes a diffusion pre-welding of material rigidly connecting the pressure-adjusted walls of the lid and the container. The method can be used for designing parts having a tensile and compression resistance, such as parts for aircraft landing gear.

Abstract: A method of fabricating an element (25) out of composite material, the element comprising three arms (22, 23, 24) arranged in a triangle. The method comprises the operations of: fabricating a three-dimensionally woven preform from reinforcing fibers and including through slots defining two arms (22, 23) and two half-arms that are all parallel and contiguous in pairs, each arm (22, 23) having one end whereby it is connected to a half-arm and another end whereby it is connected to the other arm (22, 23); shaping the preform by deploying it and by uniting its two half-arms in order to give it a triangle configuration; securing together the half-arms by stitching with reinforcing fibers; and injecting resin into the preform and polymerizing the resin.

Abstract: The invention relates to 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; and 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. According to the invention, the method further comprises the step of modifying the distribution of the wheels in response to a predetermined event occurring.

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 (1) distributing the wheels fitted with respective brakes in at least two distinct groups G1, G2, G3, G?1, G?2, G?3; (2) allocating respective braking 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 (3) acting at predetermined intervals to permutate the allocation of the relationships to the groups in application of a predefined permutation relationship. The method also includes a step of modifying the permutation relationship in response to the occurrence of a predetermined event.

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 method of fabricating a composite material part such as a link. The method comprises the successive operations of applying reinforcing fiber layers (14a, 14b, 14c) that are braided around a mandrel over all or part of the length of the mandrel, the layers being superposed one on another. The method includes a step of cutting an intermediate reinforcing fiber layer (14a, 14b, 14c) after it has been applied, a step of withdrawing a cut portion prior to applying the following braided layer (14b, 14c), thereby locally building up an extra thickness of reinforcing layers on each portion of the cut layer that has remained in place, the extra thickness constituting local reinforcement of the part. Resin is subsequently injected into the various braided layers prior to the resin being polymerized in order to prepare a blank. The method applies in particular to the field of aviation.

Abstract: An aircraft having wheels with hydraulically-actuating friction brakes and independent drives for driving the wheels in rotation and enabling the aircraft to move in stages of independent drive when engines of the aircraft are inactive. A main hydraulic circuit with a pressure source powers the brakes when the pressure source is active; with an alternative braking circuit for enabling the brake system at least when the engines of the aircraft are stopped. The alternative braking circuit includes an accumulator that is used for parking braking and is kept under pressure by the pressure source of the main circuit when the pressure source is active. An auxiliary hydraulic circuit pressurized by an auxiliary pump and power system enables the independent drives to be actuated. The auxiliary hydraulic circuit is connected to the alternative braking circuit to maintain an operating pressure in the accumulator of the alternative braking circuit.

Abstract: The invention relates to a method of managing a steering command for a steerable portion 3 of nose landing gear 2 of an aircraft 1, the method implementing servo-control to servo-control a steering actuator 6 to an angle position setpoint ?set for the steerable portion 3, the servo-control including calculating an error ? by subtracting a reference angle ?est from the angle position setpoint ?set. According to the invention, 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.