Abstract: The invention relates to a heat treatment oven comprising a loading or treatment zone, at least one gas inlet, a gas preheater chamber situated in the oven between the gas inlet and the loading or treatment zone, a susceptor comprising at least a side wall surrounding the preheater chamber and the loading or treatment zone, and a field winding suitable for heating the side wall by induction. The portion of the side wall of the susceptor that is situated around the preheater chamber presents at least two recesses spaced apart circumferentially from one another so as to form portions of reduced thickness in said portion of the side wall.

Abstract: The invention relates to an electromechanical brake, in particular for aircraft, the brake comprising a support carrying at least one electromechanical actuator comprising a pusher that is axially displaceable towards friction elements in order to apply a braking force to the friction elements, selectively, wherein the actuator is mounted on the support via a connection member allowing at least a portion of the actuator carrying the pusher to tilt angularly.

Abstract: A braking actuator for a brake of an aircraft, the actuator comprising: an electric motor; a pusher actuated by the motor; and a position sensor for sensing the position of the movable portion of the motor and provided with transmitter and receiver members. The motor has first and second exciters adapted to move the movable portion of the motor and adapted to be powered independently from each other. The transmitter member of the position sensor comprises first and second transmitters adapted to be powered independently, and the receiver member generates the signal representative of position on being excited by at least one of the transmitters.

Abstract: The invention relates to a device for selectively transmitting force, the device comprising a first element and a second element that is movably mounted on the first element, a friction member being arranged between the first element and the second element to exert a friction force between them, which force presents a maximum value that depends on prestress imparted by a presser member. The device includes control means for varying the prestress imparted by the presser member to the friction member and arranged, where appropriate, to substantially release the prestress imparted by the presser member so that the prestress becomes substantially zero.

Abstract: 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. The method comprises the steps of (1) monitoring the pressures of the tires carried by the wheels, and in response to detecting at least one of the following events: (1A) the pressure of one of the tires is less than a first predetermined threshold, and ( 1B) the difference between the pressures of two of the tires is greater than a second determined threshold; (2) activating the steering control, if the steering control is not activated; and (3) implementing a steering control relationship that is modified compared with a nominal control relationship used when the tires are properly inflated.

Abstract: The invention relates to landing gear mounted on an aircraft in such a way as to be movable between a stowed position and a deployed position, the landing gear incorporating: a barrel mounted in a hinged way on the aircraft; a folding strut with two arms; a stabilizing member to stabilize the strut in an aligned position, having two rods hinged to each other; a telescopic unlocking member having one end coupled to one of the rods, the telescopic member being selectively activatable to break an alignment of the rods. According to the invention, said rod has an aperture in which the end of the telescopic unlocking member engages and which is arranged in such a way that, when the telescopic member is activated, said end interacts with an end of the aperture to move the associated rod toward a non-aligned position which said rod reaches when the telescopic member reaches an internal stop, the aperture allowing any hinged movement of the rod beyond the non-aligned position.

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: 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 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: 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: A controlled-friction device comprising a first element having a second element mounted thereon to slide in a sliding direction, and friction retaining means arranged to exert between the two elements an opposing force against relative movement of the two elements. The friction retaining mechanism comprises a friction member mounted securely to the first element to rub against the second element via a friction surface extending parallel to the sliding direction, a presser member for exerting a thrust force on the friction member, urging the friction member against the second element in a direction normal to the relative movement of the elements, and a linkage linking the friction member to the first element causing the friction member to separate from the second element during movement in either direction of the second element relative to the first element.