Abstract: An implantable neuromodulation system can include an electrode configured to be disposed at or near a first branch of a hypoglossal nerve of a patient and configured to provide a first electrostimulation therapy to treat a sleep disorder or breathing disorder of a patient. The system can include a sensor configured to provide a sensor signal that includes information about a patient response to the first electrostimulation therapy. The patient response can include at least one of an acoustic profile of an airway of the patient, a change in a position of a tongue of the patient, and information about an evoked compound action potential (ECAP) of a portion of the hypoglossal nerve. In an example, a processor circuit can use information from the sensor signal to select a subsequent electrostimulation therapy to treat the sleep disorder or breathing disorder of the patient.

Abstract: Redundancy synchronization of remote terminal unit (RTU) central processing units (CPUs) associated with an industrial operation includes queuing time-stamped events on a main RTU CPU for transfer to a standby RTU CPU as the time-stamped events are generated on the main RTU CPU (i.e., in real-time). The synchronized RTU CPUs further permit synchronization of logic states and synchronization of firmware upgrades. Synchronization activities occur on the same synchronization communications channel between redundant RTU CPUs.

Abstract: A method and system improving energy efficiency of a turbojet engine by optimizing rotating speed of a fan and operability of an engine, by freeing the fan from exclusive control of a low-pressure (LP) shaft by providing combined control with a high-pressure (HP) shaft when cruising power has been reached. The turbojet engine include at least one LP turbine and one HP turbine coupled to coaxial LP shafts and HP shafts, respectively, which can drive LP and HP compressors, respectively. The LP compressors include a fan that forms a first primary air-intake compression stage. The LP and HP shafts are mounted on one of two driving mechanisms, an inner ring gear, and a planet carrier for a planetary gear train for driving the fan, the HP shaft being mounted on a disengagement mechanism and the fan being coupled to the planetary gear train via an outer driven ring gear.

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: A method of fabricating an aircraft landing gear rocker beam comprising a body having a clevis (24) with two lugs (19, 21) parallel to a direction that is radial relative to the body, the method comprising the steps of: forming a first mandrel; applying one or more first braided fiber layers (11) on the first mandrel; fitting a second mandrel element on the assembly as constituted in this way, the second mandrel element extending between the two lugs (19, 21) of the clevis (24) that is to be formed; applying one or more second braided fiber layers (17) on the assembly as constituted in this way; injecting resin into the various layers (11, 17) and polymerizing the resin; and machining the resulting workpiece blank in order to cut away a region of the second braided layers (17) in order to separate the two lugs (19, 21) of the clevis (24) from each other.

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: A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibers. In one embodiment, the beam takes a form of a circle arc.

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: 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 for manufacturing a straight insert intended to be incorporated in a metal container by HIC includes placing coated wires in a rectilinear juxtaposition over a predefined length in a straight gutter-shaped tool and joining the coated wires together. The insert includes a bundle of coated wires that are joined together and have a predefined length. The wires are made from metal-coated ceramic fibers.

Abstract: An apparatus includes a fitting connected to a body. The fitting has an engagement portion including a channel formed into a peripheral surface of it and an axis. The body includes an axial layer provided around at least some of the peripheral surface of the engagement portion of the end fitting and a hoop layer provided around the axial layer at a location corresponding to at least some of the channel so as to urge at least some of the axial layer into a portion of the channel. The channel is arranged such that at least some of it defines a pathway that is non-orthogonal with respect to the axis of the fitting, such that at least some of the surface area of the channel defines a load bearing surface for the transfer of torque between the fitting and body when a rotational force is applied to one of them.

Abstract: The invention relates to a method for manufacturing an arm (16) in composite material, this arm comprising a main body incorporating a bearing (22) designed to receive a shaft passing through it transversely, this method comprising the steps of: manufacturing a hub (11) by winding reinforcing fibers around a generally tubular support (12); manufacturing at least one sleeve (14); attaching the hub (11) to one end of the sleeve (14) and transversely to the sleeve (14) in order to form a mandrel; applying one or more layers of braided reinforcing fibers (21) around this mandrel with a machine for braiding reinforcing fibers (19); injecting and polymerizing resin into the layer or layers of braided fibers (21). The invention applies notably to an arm forming an undercarriage rocker arm of an aircraft.

Abstract: A method of braiding reinforcing fibers on a mandrel (8) with a machine having a ring (9) carrying at least two series of reels of fibers, by moving the mandrel at a predetermined forward speed while moving the two series of reels along the ring (9) so that they cross while rotating in opposite directions and at a predetermined speed of rotation about an axis (AX) of the ring. The braid is formed on the mandrel (8) in the vicinity of a region of convergence (R) of the fibers that together define a conical shape (C). The method comprises: a step of reconfiguring the machine in which the angle (a2) at the apex of the cone (C) defined by the fibers takes on a new value (a2); and a step of restarting braiding in which the movement of the reels along the ring (9) and the forward movement of the mandrel (8) are re-established with a new speed of rotation and a new speed of advance.

Abstract: A method of manufacturing a mechanical component, a mechanical component thus obtained, and a winding device designed for implementing the method of manufacture. The mechanical component includes at least one insert made of metal matrix composite, within which matrix ceramic fibers extend, the composite insert being obtained from a plurality of coated filaments each including a ceramic fiber coated with a metal sheath, the method including manufacturing at least one insert by winding a bonded lap or bundle of coated filaments about a component of revolution. At least some of the winding is performed in a rectilinear direction.

Abstract: A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part.

Abstract: A method of fabricating a mechanical member for aircraft, including a plurality of operations of braiding and depositing layers of braided reinforcing fibers on a mandrel (11) by using braiding machine. Each operation comprises braiding a braided layer and depositing it by moving the mandrel (11) along a central axis of the braiding machine. Each of the various superposed braided layers comprises both longitudinal fibers (12, 12G) that are parallel to a main direction of the mandrel (11), and interlacing fibers that are inclined. At least one operation is configured to form and deposit a braided layer having, in at least one cross-section of the member, a density of longitudinal fibers that differs depending on whether consideration is given to one angular region (S1) or another angular region (S2) of the same extent around the center of gravity (G) of the mandrel (11) in the section under consideration.

Abstract: A method of fabricating an aircraft landing gear rocker beam comprising a body having a clevis (24) with two lugs (19, 21) parallel to a direction that is radial relative to the body, the method comprising the steps of: forming a first mandrel; applying one or more first braided fiber layers (11) on the first mandrel; fitting a second mandrel element on the assembly as constituted in this way, the second mandrel element extending between the two lugs (19, 21) of the clevis (24) that is to be formed; applying one or more second braided fiber layers (17) on the assembly as constituted in this way; injecting resin into the various layers (11, 17) and polymerizing the resin; and machining the resulting workpiece blank in order to cut away a region of the second braided layers (17) in order to separate the two lugs (19, 21) of the clevis (24) from each other.

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: 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: 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.