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 landing gear, including an elongate axle pivotally connected to a bogie beam, the landing gear further including a locking device for locking the axle at a substantially fixed orientation with respect to the bogie beam, the locking device including first and second barrier arms that are movable between a first configuration, in which they define a barrier so as to maintain the maintain the axle in the substantially fixed orientation with respect to the bogie beam, and a second configuration, in which the axle may pivot about the bogie beam.

Abstract: The invention provides an electromechanical actuator for a vehicle brake, the actuator comprising: a motor; a screw-and-nut system having a first element, the screw or the nut, rotated by the motor; and an antirotation member preventing rotation of the second element of the screw-and-nut system, the nut or the screw, so that the second element moves linearly in response rotation of the motor so as to exert compression selectively on friction elements of the brake. According to the invention, the actuator is subdivided into a first portion comprising the screw-and-nut system, and a second portion comprising the motor, the portions being designed to be separable while the actuator is mounted on a brake.

Abstract: The invention relates to a method for powering an autonomous drive device (4) in an aircraft comprising a certain number of drive motors (5) for the wheels (6) when the jet engines of the aircraft are not activated, the aircraft comprising an auxiliary power unit or APU (2) driving a first generator (1) for supplying power to devices on the aircraft that need to be powered when the jet engines are not activated, characterized in that the method comprises the use of a second generator (8) dedicated to the power supply of the autonomous drive device, the second generator being disposed in parallel with the first generator so as to be driven by the APU and, when it operates as a motor under the action of power recovered by the autonomous drive device, so as to help the APU drive at least the first generator.

Abstract: The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors.

Abstract: An aircraft landing gear including a fairing (12) arranged to be moveable between first and second configurations, wherein in the first configuration the fairing shields an element of the landing gear from an incident airflow, the fairing being arranged to be in the first configuration when the landing gear is deployed but unloaded, and wherein in the second configuration the fairing exposes the landing gear element to the incident airflow, the fairing being arranged to be in the second configuration when the landing gear is deployed and loaded.

Abstract: A method for efficient, industrialisable detection of machining burns of VHS steel. Machined steel is immersed in an aqueous solution of acids including hydrofluoric acid and nitric acid. To define a burn degree, a color chart for calibrating machining burns of VHS steel detected using the method is prepared. The color chart can include studs of the examined steel subjected to deliberate damage by excessive resurfacing actions (or other machining modes), then submerged in the acid solution. The resurfacing actions can be simulated by overheated thermal treatment, between an ageing temperature (for example 510° C. for steel) and a solution annealing temperature (950° C. for the steel). The samples are classified according to the grey level thereof resulting from the immersion and corresponding to a predetermined hardness and thus to a predetermined level of damage.

Abstract: The invention provides a method of managing the braking of an aircraft having a plurality of brakes comprising friction elements, the method comprising the following steps for at least one group of brakes: estimating an energy level (?E) to be dissipated by the brakes of the group; and estimating individual braking setpoints (Fi) for each of the brakes of the group so that the individual braking setpoints make it possible, at least under normal operating conditions of the brakes, to implement braking that dissipates said energy level, the individual braking setpoints also being determined so as to satisfy at least one other given operating objective.

Abstract: Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.

Abstract: The invention relates to a method of fabricating a composite material part in which one or more layers of braided, or woven, or indeed draped reinforcing fibers are applied onto a mandrel having the general shape of a body of revolution. After one or more layers have been applied onto the mandrel, an operation is performed of winding at least one tie helically around and along the assembly constituted by the mandrel and each layer of reinforcing fibers that it carries, so as to press each layer of reinforcing fibers against the mandrel. The invention relates to fabricating composite material parts such as beams, connecting rods, or arms made out of carbon fibers.

Abstract: An aircraft braking system architecture having brakes with electromechanical actuators (3) for selectively applying a braking force to respective stacks of disks (2) in order to exert a braking torque on respective wheels. Included is at least one power module (7) that sends phase currents to the electromechanical actuators so that the latter can exert a braking force and at least one control module (8) for controlling the power module in response to a braking command such that appropriate phase currents are sent to the actuators so that these can develop the desired braking force. At least one power supply unit (20), comprising means (21) of generating a high voltage (HVDC), supplies the power module with the high power it needs for powering the actuators. The unit (20) also has means (22) for generating a low voltage (LVDC) for powering at least the control module at a low voltage.

Abstract: A method for distributing braking energy between a group of braked wheels 1 . . . p and fitted to N undercarriages of an aircraft, each of the braked wheels comprising a brake furnished with a stack of discs to which a load is selectively applied so as to generate a torque for braking the wheel. Each brake is equipped with means for measuring a thickness of the stack of discs, and in which: the setting C j = E j E 1 + … + E p . N . C is assigned as individual setting of braking to be generated by brake j. Here, p is the number of wheels concerned, C is the general setting of braking to be developed by the braked wheels of the same undercarriage, Ej is the thickness of the stack of discs of the brake of wheel j, and Cj the individual braking setting for wheel j. Each brake is controlled according to the individual braking setting thus determined.

Abstract: The invention relates to a power supply having two inverters (A, B) in series for powering an electromechanical actuator having an electric motor including a plurality of windings (R1, R2, R3) forming phases, each inverter being connected to its own ground (50; 51) and having a voltage source (U1; U2) having as many arms (A1, A2, A3; B1, B2, B3) as there are windings to be powered, each arm including two controlled switches (5, 6) connected in series, with a point therebetween being provided for connection to one end of one of the windings. According to the invention, each inverter includes an additional arm (A4; B4) having two controlled switches, the two additional arms being interconnected by a bridge (7) that is connected to each of the additional arms at a point that is situated between the switches.

Abstract: The invention relates to a stabilizer suitable for stabilizing disks of a heat pack, wherein the stabilizer includes at least two elongate parallel pushers of height compatible with the height of the heat pack, each movable in a direction perpendicular to the pushers, the pushers being associated with an irreversible driver system enabling the pushers to be moved apart or towards each other, the pushers extending in service so as to face an inside diameter of the disks.

Abstract: The invention relates to a method of controlling a vehicle brake that is adapted to exert a braking force in response to an actuation setpoint, the method comprising the following steps: from a braking setpoint, determining a nominal actuation setpoint for the brake actuator, taking account of all of the components of the braking setpoint; from the same braking setpoint, and from a measurement of the torque developed by the brake, determining a correction for the nominal actuation setpoint, this correction taking account only of low-frequency variations in the braking setpoint; and adding the correction to the nominal setpoint.

Abstract: A telescopic actuator comprising a cylinder in which a main rod is mounted to slide telescopically along a sliding axis (X) between a retracted position and an extended position. The actuator includes an auxiliary rod mounted to slide in the main rod along the sliding axis between retracted and extended positions. A structure is provided for retaining the auxiliary rod in the retracted position inside the main rod. There also is a brake structure for braking sliding of the auxiliary rod in the main rod in the extension direction. The auxiliary rod has a thread on an outside surface, and the main rod has a rotary bearing that centers the auxiliary rod inside the main rod and co-operates via a reversible helical connection with the thread of the auxiliary rod such that extension of the auxiliary rod causes the rotary bearing to rotate.

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 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: One or more two-dimensional fiber fabrics of carbon or carbon precursor fibers are impregnated (58, 59) by a solution or a suspension capable of allowing a dispersion of discrete ceramic particles to remain in the fiber fabric, and a fiber preform (51) is made by superposing plies formed of two-dimensional fabric made of carbon or carbon precursor fibers, the plies being bonded to one another, and at least some of the plies being at least partially formed of a previously-impregnated two-dimensional fabric. The field of application is particularly that of friction parts made of C/C composite material with incorporated ceramic particles.

Abstract: A hydraulic actuator comprising a hollow body (1, 3) defining a cylindrical cavity and a rod (5) 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 (C1, C2). The rod defines an interior passage, connecting the two chambers, which has a valve (20) comprising a shut-off member (21) which is returned towards a seat (22) and closes the passage. The rod receives a push member (15, 26) which can move relative to the rod between a position apart from the shut-off member (21) 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 (3) of the hollow body.