Abstract: A strut for an aircraft landing gear is provided. The strut includes a casing configured to absorb landing forces applied to the aircraft landing gear. The casing includes a cavity in which an energy accumulator is housed. The energy accumulator can be a removable cartridge which can be inserted in the cavity. An aircraft landing gear comprising such a strut is also provided. An aircraft comprising at least one such landing gear having such a strut is also provided. A method for emergency deployment of such a landing gear, using energy stored in the energy accumulator integrated in the strut of the landing gear to deploy the landing gear is also provided.

Abstract: A high-voltage DC electrical distribution plate with two integrated electromechanical power contactors. Chambers of fixed and movable contact terminals of the two contactors are disposed on a first of the major surfaces of the plate, while on the second major surface of the plate are disposed complementary assemblies of the two contactors, each complementary assembly including a motor intended to activate the contact terminals of the contactor in question. The other components disposed on the second major surface of the plate leave a free space constituting an area of attachment of the complementary assemblies of the two contactors, this area being dimensioned to allow the arrangement of the complementary assemblies of the contactors in two orthogonal orientations allowing the motors to activate contact terminals of different sub-assemblies of the contact chambers and thus to make the parallel or series configurations of the contactors.

Abstract: A turbomachine includes a low-pressure shaft having an internal passage for a first air stream and a first segment. A second segment includes a first frustoconical portion, and an intermediate lubrication chamber wherein at least one bearing is arranged. The intermediate lubrication chamber is arranged in an intermediate casing. An annular air chamber is configured to be supplied with air from a low-pressure compressor and is at least partly axially delimited by the first frustoconical portion. A radial separating wall is mounted around the first segment, and the first frustoconical portion further includes an opening to enable the first air stream to pass from the air chamber to the internal passage.

Abstract: A DC electrical power distribution device for an aircraft propulsion duct having a main power supply line configured to supply at least one propulsion assembly of the propulsion duct with power from a high-voltage DC electrical power supply source and including main switching means and fast switching means for connecting the source to the propulsion assembly. The device can include a secondary power supply line configured to be connected to another distribution device and configured to supply the propulsion assembly with power from the other device when the main switching means are open.

Abstract: The present application describes a method for joining two anodized elements by friction stir welding. This method for joining a first element to a second element comprises a step of anodizing the first element, a step of anodizing the second element, and a step of producing a weld seam by friction stir welding the first element to the second element.

Abstract: An intermediate assembly for additive manufacturing includes a metal part with an overhang portion. The intermediate assembly further includes a support structure for the overhang portion, wherein the support structure includes a fusible, porous connecting portion extending from the overhang portion, a baseplate extending from the connecting portion and defining a plurality of channels, and at least one column carrying the baseplate.

Abstract: An injection mold for the manufacture of an axisymmetric part of composite material comprising a mandrel supporting a fibrous preform and comprising an annular wall, and a plurality of counter-mold angular sectors assembled to the mandrel and intended to close the mold and to compact the fibrous preform wound on the mandrel. Each angular sector comprises an annular base intended to come into contact with the fibrous preform. The plurality of angular sectors includes a first series of angular sectors and a second series of angular sectors, first and second lateral edges of the first series of sectors each including a protruding lower portion, the first and the second lateral edges of the second series of sectors each including a recessed lower portion.

Abstract: A cooling system for a drive device with several electric machines, the cooling system including a hydraulic circuit for a coolant including a cooling part in a gearbox of the drive device for cooling the gearbox, and an air/coolant heat exchanger including cooling walls forming channels for circulating coolant for the cooling thereof, an air cooling circuit including a plurality of fans, rotationally coupled to the gearbox, a cooling part between the cooling walls of the air/liquid heat exchanger, wherein the air sucked in and propelled by the fans circulates by sweeping over the cooling walls in order to cool them.

Abstract: An unducted rectifier for a turbomachine is provided. The rectifier includes: (1) stator vanes each having a root and a blade radially projecting from the root, the root having two half-platforms; (2) pivots, each associated with a vane mounted so as to pivot about a pitch axis and configured to connect to a system for changing the pitch of the blades, each pivot having an upper platform and a cylindrical lower portion; and (3) attachment systems for attaching the half-platforms of the root of the vane to the associated pivot, each having two plates having a substantially identical shape to each half-platform and a clamping system for clamping the half-platforms between the plates of the attachment system and the upper platform of the pivot.

Abstract: A rotor wheel for an aircraft turbine engine has a disc with a main axis and cells at its outer periphery. The cells extend along the axis, and each has a bottom and two side flanks. Vanes are mounted in the cells of the disc, each vane including a blade connected by a platform to a root mounted in one of the cells. Each root includes, at its radially inner end, a lobe with a first axial end having a circumferential notch and a second axial end having a radially inward facing stop configured to axially bear on a first face of the disc. An annular ring engages the notches of the vanes and is axially clamped against a second face of the disc. Each lobe has a radially inward facing projecting bulb configured to radially bear on the surface of the bottom of the corresponding cell.

Abstract: Described is a passenger seat having a seat member moveable between a stowed position and a deployed position and at least one actuator coupled to at least one portion of the seat member, wherein the at least one actuator is activable without direct contact with a passenger's hand to change a lock state of the seat member, and wherein an unlocked state of the seat member permits movement of the seat member between the stowed position and the deployed position.

Abstract: The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air within a secondary duct (16), the gas generator (5) being connected to a fan casing (3) by a stator blade assembly (40) that passes through the secondary duct, first openings (28) for letting in air from the reverse flow being located on an outer casing (17) at least partially internally delimiting the outer duct, and second openings (29) for letting said air out being located on an inner casing (14) at least partially externally delimiting an inner duct (12). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.

Abstract: The invention relates to a turbine blade (33) for a movable wheel of a low-pressure turbine of an aeronautical propulsion system, comprising a root (331), a shroud (334), and an aerodynamically profiled airfoil (333) extending from the root (331) to the shroud (334), wherein a parameter N2S is defined as: N ? 2 ? S = ? ? ( R ? e 2 - Ri 2 ) × w 2 , where: Re is an outer flowpath radius, Ri is an inner flowpath radius, w is a limit rotation speed of the drive shaft, wherein the outer flowpath radius Re and the inner flowpath radius Ri are chosen such that N2S is greater than a certain threshold which depends on the temperature T measured when the drive shaft rotates at the limit rotation speed w.

Abstract: Disclosed is an assembly for a turbomachine comprising: ?—a second connection element (8) having a third end (81) which is connected to a turbine shaft (2) and is mounted on a second bearing (5), and a fourth end (82) connected to a mechanical transmission device (6), the second connection element (8) having a second radial compliance (SR2); and ?—a third connection element (9) having a fifth end (91) fixedly mounted on a casing (1), and a sixth end (92) connected to the mechanical transmission device (6), the third connection element (9) having a third radial compliance (SR3), wherein a ratio of the first radial compliance (SR1) to the third radial compliance (SR3) is strictly lower than 10% and/or a ratio of the first radial compliance (SR1) to the second radial compliance (SR2) is strictly lower than 4%.

Abstract: The present invention relates to a method and a device for recording radiofrequency activity of artificial satellites orbiting the Earth and emitting electromagnetic signals, characterized in that the device contains an antenna for receiving an acquisition signal, a reception chain, a computer able to compute the power spectral density on at least one frequency sub-band based on the signal, a control device for pointing the line of sight of the antenna at at least one sequence of prescribed orbital positions that are successive and separate from one another.

Abstract: The invention relates to a secondary flow stator vane (1) for a turbomachine, comprising skins (2, 3) having end portions (21, 31) delimiting an opening (5) and a cavity (4) therebetween, which skins diverge from one another in a direction (Y). A filler material (41) is located in the cavity (4) at a distance from the opening (5). A reinforcement (6), the density of which is higher than the density of the material (41), comprises a first reinforcement portion (61) located in the cavity (4) against the material (41) and a second reinforcement portion (62) for closing the opening (5) between the portions (21, 31) to form a single piece.

Abstract: A brake assembly is configured for use with a wheel in an ambient environment. The wheel includes a rim rotatably mounted to an axle. The brake assembly includes a brake stack and an actuation assembly configured to selectively apply a force to the brake stack. A cover sealingly engaged the rim to at least partially define a fluidic barrier between a brake cavity and the ambient environment. The brake stack is located within the brake cavity.

Abstract: A turbofan including a fan, at least one annular casing surrounding the fan and elements being fastened to an outer surface of the casing via a fastening assembly, the elements including a first elastic member arranged for urging the first end of the support away from the casing, and a first return member (27) arranged for resiliently urging the first end towards the casing, and a second elastic member (25) arranged for urging the second end of the support away from the casing, and a second return member (29) arranged for resiliently urging the second end towards the casing.

Abstract: A gutter for recovering lubrication oil, particularly for a mechanical reducer, comprising un corps principal comprising an annular main body around a central axis, and a deflector attached to the main body and configured to allow the evacuation of the oil radially from an inner cavity of the main body toward the outside of the gutter, the deflector comprising a main sleeve disposed in the extension of the main body, and an evacuation channel configured to deflect oil from the main sleeve and having a curved shape such that a first end of the evacuation channel, communicating with the inner cavity, is tangent to the main body, and a second end of the evacuation channel is directed outward with respect to the annular main body.

Abstract: Disclosed is an aircraft turbine engine (10), comprising a gas generator (12) and a fan (14) arranged upstream from the gas generator (12) and configured to generate a gas inlet stream (F), part of which flows into a duct of the gas generator to form a primary stream (36), the turbine engine (10) comprising an electrical machine that is mounted coaxially downstream from the fan (14) and that comprises a rotor (62a) surrounded by a stator (62b) carried by an annular shroud (64), this shroud (64) being surrounded by a casing (40) of the gas generator that defines, with this shroud (64), a section of the flow duct for the primary stream (36), stationary vanes (42, 68) for straightening this primary stream (36) extending into this path.