Abstract: A passenger seat headrest includes a body and a side wing. The body includes a forward side, an aft side distal from the forward side, a first side extending between the forward side and the aft side, and a second side distal from the first side and extending between the forward side and the aft side. The side wing is pivotably connected to the first side of the body and is pivotable between a stowed position, at which the side wing is positioned against the forward side of the body, and a deployed position, at which the side wing is spaced apart from the forward side of the body.

Abstract: An annular combustion chamber of a turbomachine is described. The combustion chamber has an axis of revolution and is delimited by coaxial internal and external annular walls joined upstream by a bottom of chamber substantially transverse to the walls. In some embodiments, the chamber includes at least one annular deflector placed in the chamber and substantially parallel to the bottom of chamber. The bottom of chamber may have openings adapted to be traversed by air for cooling the deflector. In some embodiments, the bottom of chamber and the deflector include mounting openings for mounting an annular row of injection devices for injecting a mixture of air and fuel into the chamber. At least a portion of the air for cooling the deflector is conveyed into the chamber through holes in the injection devices.

Abstract: An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.

Abstract: Method implemented in a system comprising a control station and at least one drone. Each data communication in said system between the control station and a drone taking place in the form of packets, each packet comprising a preamble and being transmitted in a form modulated according to a predefined modulation. The method comprises: using, in each packet communication from the control station to a drone, a so-called uplink preamble, orthogonal to the so-called downlink preamble, used in each packet communication from a drone to the control station; and, on reception of a modulated packet, determining whether said modulated packet has been transmitted in the context of an uplink or downlink communication according to a result of a convolution between said modulated packet with a reference preamble modulated according to the predefined modulation, said reference preamble corresponding to the uplink preamble or to the downlink preamble.

Abstract: A moulding unit for producing a turbomachine blade blank. The moulding unit has an upstream portion and a downstream portion. According to the invention, the moulding unit comprises a raised portion designed to form a downstream opening which, at the level of the trailing edge, passes through at least one of the side edges of the basin-like portion at the blade tip. The raised portion rigidly secures the upstream portion to the downstream portion and comprises a strengthening protuberance extending in the transverse direction.

Abstract: An epicyclic gear device for driving rotation of a first blade set of a turbine engine, the device: including a sunwheel centered on a longitudinal axis of the turbine engine and connected to a rotor of the engine in order to be driven in rotation; at least one planet meshing with the sunwheel; a planet carrier rotatably carrying the planet and connected to a first blade set in order to drive it in rotation; and a ring meshing with the planet; the sunwheel being connected to the rotor via a first constant velocity ball transmission joint.

Abstract: The invention relates to a clamping system (1) comprising a clamping jaw (7) mounted on the shaft of a pneumatic or hydraulic cylinder (4), wherein said cylinder has a structure which drives the clamping jaw towards its clamping position when the pneumatic or hydraulic energy supply of the cylinder is interrupted, the pneumatic or hydraulic energy supply of the cylinder opposing the clamping, and where means (8) are provided for locking the cylinder when the clamping jaw is in a non-clamped position.

Abstract: A modular auxiliary switch includes a housing including a first housing part and a separate second housing part secured to the first housing part. A printed circuit board is housed in one of the first and second housing parts, and has a first side facing the first housing part and a second opposite side facing the second housing part. An actuator mechanism is housed in the first housing part and is coupled to the printed circuit board. A separate first electrical contactor is selectively mounted to the printed circuit board so that a first electrical contact surface of the first electrical contactor overlaps and is in direct contact with one of the first side and the second side to define a first electrical contact pad on the printed circuit board.

Abstract: A method for the acoustic analysis of a machine (M) including the acquisition of at least one acoustic signal supplied by at least one microphone (7) positioned in the machine, characterized in that it comprises the following steps: separation of at least one acoustic signal into a plurality of sound sources, the signal being modelled as a mixture of components, each one corresponding to a sound source; for at least one separated sound source, determination of a characteristic acoustic signature; comparison of at least one characteristic acoustic signature with at least one reference acoustic signature recorded in a reference database (5).

Abstract: A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade.

Abstract: A device for de-icing a splitter nose of an aviation turbine engine, the device including a splitter nose having an outer annular wall defining the inside of the bypass stream flow channel and an inner annular wall defining an inlet of the core stream flow channel, and an inner shroud mounted at its upstream end on the inner annular wall of the splitter nose and designed to have inlet guide vanes fastened thereto, the splitter nose and the inner shroud defining an annular volume. The device includes an annular deflector positioned inside the annular volume so as to subdivide the annular volume into a first annular cavity and a second annular cavity, the second annular cavity being defined between the annular deflector and the outer annular wall of the splitter nose.

Abstract: A control system for controlling the pitch of a propeller, the system including a propeller shaft, a blade swivel device having a rotary control element suitable for placing the blades in an angular position corresponding to a desired propeller pitch, and a transmission presenting an outlet member coupled in rotation with the rotary control element of the blade swivel device. The transmission includes a variable speed drive having drive, control, and outlet rotors that are coupled in rotation respectively with the propeller shaft, with a control member, and with the outlet member of the transmission. With the variable speed drive, the speed of rotation of the outlet member of the transmission is a predetermined function of the speeds of rotation not only of the propeller shaft, but also of the control member.

Abstract: The invention relates mainly to a seat module intended to be installed in an aircraft cabin, having a seat and a tray table that is movable between a folded position and a deployed position, wherein the tray table is also movable in translation and/or in rotation with respect to the seat in order to be moved from the deployed position to an offset deployed position.

Abstract: A method for nondestructively testing a part comprising an elongate microstructure is disclosed.

Abstract: An aircraft turbine engine has a pair of rotating and non-ducted propellers. An upstream propeller has an outer diameter D1 and a downstream propeller has an outer diameter D2. The engine further includes a system for varying the diameter D2. The downstream propeller includes an annular row of blades, each of which is configured to be mounted telescopically in the radial direction (R) in an outer fan duct.

Abstract: A passenger seat, such as an aircraft passenger seat, includes a seat base and an entertainment system. The seat base includes a cushioning member and a cover covering the cushioning member. The entertainment system is positioned between the cushioning member and the cover and is removably connected to the cushioning member. The entertainment system is configured to determine a force caused by a passenger's legs in at least two locations on an upper surface of the seat base when used.

Abstract: The invention relates to an autonomous device (10) for storing and releasing energy in order to power a piece of electrical equipment (12), in particular a piece of electrical equipment (12) of an aircraft, characterised in that said device comprises: a first means (16), configured to transform a variation in the surrounding pressure (P) to which the device (10) is subject into mechanical energy, at least one second means (20, 22), configured to mechanically store said mechanical energy by transforming same into the form of mechanical potential energy, a third means (24), configured to control the release of the mechanical potential energy contained in said second means (20, 22) and transform same into restored mechanical energy, a fourth means (28), configured to transform the restored mechanical energy into electrical energy suitable for powering said piece of electrical equipment (12).

Abstract: A method of fabricating a reinforcing edge (10?) of a turbine engine blade (70) in which there is provided a blank (10) of the reinforcing edge and an indentation is imprinted in said blank so as to form a rough surface (S). A reinforcing edge (10?) obtained by such a method.

Abstract: A rotating inlet cowl for a turbomachine, comprises a cone, a shell and a plug. The plug comprises an external wall with an external surface that will form an aerodynamic profile in continuity with an external surface of an external wall of the cone, when the external wall closes off a cavity that is formed between the external wall of the cone and the shell. The plug comprises an internal wall of the support and an attachment device. The attachment device is configured to pass through the support and to rigidly fix the support wall to an internal wall of the cone and the internal wall of the cone to the shell simultaneously, through an orifice in the external wall.

Abstract: The invention relates to a method for mounting an engine (1) on an aircraft strut (3) comprising engine suspension members (31) integral with the strut, the engine being integral with a suspension cradle (6) whereby it is suspended from the strut, the method comprising a step of hoisting the engine in a vertical direction as far as the strut then a step of approaching the strut by a movement of the engine in another direction, characterised in that an intermediate part (7) is fixed to the strut beforehand, by attaching it to said suspension members (31), said intermediate part (7) having an interface intended to cooperate with a complementary interface provided on the cradle (6), in such a way as to position the cradle relative to the intermediate part at the end of the approach movement to the strut. The invention also relates to the system for implementing the method.