Abstract: A landing gear system includes wheel rotatably coupled to an axle. A driveshaft extends through a cavity formed in the axle and is rotatable about an axis. A planetary gear includes a sun gear operably coupled to the drive shaft and a planet gear operably engaging the sun gear. The planetary gear further includes a ring gear that surrounds and is operably coupled to the planet gear so that rotation of the drive shaft rotates the ring gear. A clutch assembly is selectively moveable between an engaged state and a disengaged state. The clutch assembly transfers rotation of the ring gear to the wheel when the clutch assembly is in the engaged state, and the clutch assembly does not transfer rotation of the wheel to the ring gear when the clutch assembly is in the disengaged state.

Abstract: An aircraft landing gear assembly includes a main fitting comprising having a main barrel and a cross beam fixedly positioned relative to the main barrel and extending radially from the main barrel. The main fitting further includes a drag arm with a first end pivotally coupled to the cross beam by a first pivotal connection and a second end pivotally coupled to the main barrel by a second pivotal connection.

Abstract: A pivot (14) with a longitudinal axis (Y) for a bearing of a mechanical reduction gear, comprising a first annular part (14a) including an axial passage (17) and a second annular part (14b) mounted around the first annular part (14a), the first annular part (14a) delimiting with the second annular part (14b) a lubrication circuit at least one oil inlet (20) of which opens out inwards of the first annular part (14a) into the axial passage (17) and at least one oil outlet (28) of which opens radially outwards of the second annular part (14b).

Abstract: The invention relates to a blade pivot with adjustable orientation for a turbomachine fan hub, comprising: a stud having a fastener configured to retain a blade root and coupling means for the transmission of a twist torque; a ball bearing for taking centrifugal forces having an inner ring and an outer ring; a first clamping nut intended to be screwed on an inner thread of the hub to ensure clamping of the outer ring of the ball bearing; a rolling-element bearing for taking transverse forces having an inner ring and a smooth outer ring; a locking ring mounted between these two inner rings to provide for them a respective transverse support; an anti-rupture sleeve carrying the inner ring of the rolling-element bearing for taking transverse forces and the terminal end of which is extended transversely beyond the outer ring of this bearing.

Abstract: A device for connecting an electric wiring harness to the rear of an electrical connector, includes two half-shells configured to be assembled and to receive within them at least one cable of the electric wiring harness, a rear clamping nut designed to compress the two half-shells radially around the cable, a longitudinal body designed to hold the two half-shells axially, a front clamping nut designed to hold the longitudinal body around the electrical connector, wherein each one of the two half-shells includes an inner pad made of an elastomeric material, configured to be in contact with the cable, and an outer jacket made of a rigid material, at least partially enveloping the inner pad and configured to be in contact with the rear clamping nut.

Abstract: The production of a device for holding one or more electrodes for electrical discharge machining, comprising a body having a rectilinear portion in which at least one first duct is provided for the passage of one or more electrode(s). The body further has an integral curved portion in which (at least) one second curved dielectric fluid supply duct is provided and in which is provided a curved extension of said at least one first duct. The curved extension and the second curved duct are made of ceramic, with an inner mean roughness of: Ra<2 ?m.

Abstract: Discharge grate intended to be mounted inside or at the outlet of a conduit of a discharge valve of a turbine engine of an aircraft, the discharge grate comprising an upstream face intended to receive a gas flow, a downstream face parallel to the upstream face and intended to deliver the gas flow received on the upstream face, and orifices passing through the perforated plate from the upstream face to the downstream face and intended to convey the gas flow through the perforated plate. The discharge grate comprises for each orifice of the perforated plate a tubular channel, coaxial with the orifice with which it is associated, and projecting from the downstream face of the perforated plate.

Abstract: An upstream rail of a turbine engine turbine casing, which includes a casing body extending along a longitudinal axis, includes a base including a radial face, extending substantially radially from the casing body, a plate including an upper face, extending substantially along the longitudinal axis, a connection portion between the base and the plate, including a concave face connecting the radial and upper faces, the concave and radial faces extending on either side of an edge. The upstream rail is repaired through a method including covering a surface with a solder, the surface including the upper and concave faces such that the solder extends until the edge, and machining the covered surface, in a single action, in a direction toward the radial face, so as to reshape the surface, wherein the machining of the covered surface is performed on a portion of the radial face.

Abstract: The invention relates to a method for characterizing, from a volume image, a fibrous structure having a three-dimensional weaving between a plurality of warp yarns extending along a first direction and a plurality of weft yarns extending along a second direction perpendicular to the first one, the method comprising: a first processing (E10) of the volume image by filtering along a third direction perpendicular to the first and second directions so as to attenuate the periodic patterns along the third direction, obtaining (E20) a two-dimensional image corresponding to an intermediate plane along the third direction of the filtered volume image, a second processing (E31, E41) of the two-dimensional image by filtering along the first or second direction so as to attenuate the periodic patterns, obtaining (E32, E33) a one-dimensional profile representing the positions of warp or weft columns and corresponding to an intermediate line along the first or second direction of the filtered two-dimensional image, and co

Abstract: A braking system architecture for aircraft, the architecture comprising: a brake (20) comprising a plurality of electromechanical actuators (26), each electromechanical actuator including a digital communication module; at least one power supply unit (21, 22); two control units (23, 24), each control unit being connected to a distinct group of one or more electromechanical actuators and comprising an upstream digital communication module (27), a control module (28) arranged to generate digital control signals (Sn1, Sn2), and a downstream digital communication module (29) connected to the digital communication modules of the electromechanical actuators of said group in order to transmit the digital control signals to the power modules of said electromechanical actuators; and a digital communication network (25) to which the upstream digital communication modules (27) of both control units are connected.

Abstract: The invention relates to a method for detecting events by reflectometry in an electrical line of an avionic system, said line being fed with an AC voltage at a first frequency (f1), said AC voltage being sinusoidal and composed of a succession of alternate half-periods, said method comprising a step of injecting a reflectometry signal into the network, the reflectometry signal having a second frequency (f2) higher than the first frequency (f1); wherein the injecting step is synchronized with the AC voltage, the injecting step being carried out by injecting the reflectometry signal into the network during an injection duration (ti) comprised between the start and end of a half-period (t1) of the AC feed voltage.

Abstract: The method of preparing a navigation autonomy map for a vehicle covering a zone including path segments, comprising the following steps: identifying the path segments for which the map needs to be prepared; for each path segment, calculating a primary autonomy index in accordance with at least two distinct functions; and calculating for each path segment a final autonomy index by taking a weighted average of the primary autonomy indices. An autonomy map, an application of the autonomy map, and a vehicle using such an autonomy map.

Abstract: A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.

Abstract: Described are support assemblies for a passenger seat, that can include a supportive surface configured to connect with a frame of a passenger seat, and shaped to support a passenger. Supportive surfaces can include a first portion formed of a first plurality of cells having an auxetic cell geometry that can deform to adopt a synclastic curvature under stress, and a second portion formed of a second plurality of cells having a non-auxetic cell geometry that can deform to adopt an anticlastic or cylindrical curvature under stress. The regions having respective auxetic and non-auxetic cell geometries can be arranged to form a supportive surface that can flex to follow contours of a seated passenger.

Abstract: The invention concerns a method for coating a core (1) for producing a turbomachine part (2) by isostatic compacting, for example a leading-edge shield of a blade, the coating method comprising the steps of:—S1: covering the core (1) by means of a first solution comprising a first refractory component configured to oppose the diffusion of species, the first component comprising a metal oxide,—S2: covering the core (1) by means of a second solution comprising a second component designed to bind the first component in such a way as to form a homogeneous layer, the second component comprising a mineral binder;—S3: applying a heat treatment to the covered core (1) in such a way as to dry the solution and solidify the coating.

Abstract: Passenger seat assemblies may be used in vehicles such as aircraft. The passenger seat assembly includes a first wall, a second wall opposite from the first wall, and a passenger seat having a first side and a second side opposite from the first side. The passenger seat is positioned between the first wall and the second wall. The passenger seat assembly is positionable between a forward-facing configuration and an aft-facing configuration. In both the forward-facing configuration and the aft-facing configuration, the first wall is proximate to the first side of the passenger seat and the second wall is proximate to the second side of the passenger seat.

Abstract: Device for manufacturing a part using a method of selective fusion or selective sintering on a powder bed comprising a build plate having a working surface, parallel to a first direction and to a second direction, on which surface the part is intended to be manufactured, a wiper which is placed on the working surface and capable of moving and spreading the powder in the first direction on the working surface, characterized in that it further includes at least two acoustic sensors which are fixed and spaced in the second direction on the wiper and capable of detecting an acoustic signal; a laser range finder pointing in the first direction and capable of determining a position of the wiper in the first direction; and a control system capable of detecting an anomaly on the basis of said acoustic signal and of determining a position of the anomaly.

Abstract: An aircraft turbomachine having a centrifugal compressor, an annular combustion chamber, an annular casing extending around the chamber and delimiting an annular space (E) in which the chamber is situated, and a heat exchanger. The heat exchanger can include a first circuit supplied with exhaust gas from the turbomachine, and a second circuit connected by first and second volutes respectively to an outlet of the compressor and to the annular space. The first and second volutes can be positioned at an axial distance from one another, and the second volute is can be connected to the annular space by a straightener which is situated at least in part outside the casing and which is integrated into an annular connecting pipe which connects the second volute to this casing.

Abstract: A movable close-out shroud suitably configured to substantially cover, partially block, or otherwise close out an articulating opening to a cavity, void, etc., of a first part, such as a passenger seat section. The close-out shroud is configured to move between a stored position and a close-out position.

Abstract: An intermediate casing includes an inner wall having an outer surface extending along a longitudinal axis, the outer surface having a first profile in a first plane, an outer wall having an inner surface a second profile in the first plane, and first through fourth arms each extending radially. The outer and inner surfaces and the first and second arms delimit a first cavity, the first cavity having a first area and the outer and inner surfaces being separated by a first distance. The outer and inner surfaces and the third and fourth arms delimit a second cavity, the second cavity having a second area and the outer and inner surfaces being separated by a second distance. The first and second profiles are such that the first area is substantially identical to the second area and the first distance is different from the second distance.