Abstract: The invention relates to a method for processing a radionavigation signal generated by a satellite (SAT), said method comprising the following steps implemented in a processing unit of a radionavigation receiver: converting (102) the radionavigation signal into the frequency domain by means of a complex Fourier transform so as to obtain a frequency-domain radionavigation signal comprising a real part I and an imaginary part Q, the real part I having an amplitude I2 associated with one frequency; determining (103) a distribution law of the amplitude I2 of the real component I of the frequency-domain radionavigation signal; determining (104) an amplitude of the real component for which the distribution function is zero, said amplitude defining a threshold; processing (105) the frequency-domain radionavigation signal so as to filter components the amplitude of which is higher than the determined threshold.

Abstract: An acoustic panel for an aircraft comprising: a sound attenuating sheet having a plurality of cavities, a sound attenuating sheet having a first surface, a second surface opposite to the first surface and an end surface connecting the first and second surfaces, a first sheet extending over at least a portion of the first surface and over the end surface, and a second sheet extending over the second surface and the end surface, wherein the first and the second sheets are connected such that a tensile force can be transferred therebetween.

Abstract: A silicon heating mat, the mat being formable and deformable and including a matrix made of elastic material, in which at least one cavity is arranged that fully passes through the matrix, the at least one cavity being intended to accommodate a resistive filament connected to a heating cycles management unit. Furthermore, the at least one cavity has an undulating layout, with each resistive filament being able to move inside said at least one cavity, and each resistive filament having a zigzag or spiral shape.

Abstract: A variable speed constant frequency electric voltage regulation circuit may include a slow voltage loop detecting and adjust an amplitude of an output signal of the circuit. A fast voltage loop of the circuit may include an error amplifier detecting a difference between a reference sine wave signal and the output signal. A current control loop may include a current controller and an inverter. A first switch may toggle a gain of the circuit between a gain associated with a normal mode and a gain associated with a power transfer mode based on a power transfer command signal. A second switch may toggle control between the current control loop in the power transfer mode and the fast and slow voltage loops in the normal mode. The sample/hold circuit eliminates the slow voltage loop from regulating the output during the power transfer.

Abstract: An aircraft brake system comprising: a first group of at least one electromechanical actuator, a second group of at least one electromechanical actuator, a first control device with a first software module and a second software module, the second software module being configured to control the first group of at least one actuator at least in the event of a fault of the first software module, a second control device with a third software module and a fourth software module, the fourth software module being configured to control the second group of at least one actuator at least in the event of a fault of the third software module, wherein the first device module and the second control device are dissimilar. The invention also relates to an aircraft equipped with this system.

Abstract: A method for automatic quality inspection of an aeronautical part, includes detecting faults on an image of the aeronautical part using a trained artificial neural network; training an auto-encoder on a database, by projecting each image of the database onto a small mathematical space in which the images follow a predefined probability law; for each image of the database, calculating a plurality of metrics; supervised training of a classifier from the calculated metrics; detecting faults or anomalies in the image of the aeronautical part using the auto-encoder and the classifier.

Abstract: A thrust reverser includes a jack for translational actuation of a movable part, the jack being a screw jack without an extension tube.

Abstract: An attachment assembly for an aircraft strut mounting joint. The attachment assembly includes a tubular structure having a central axis and at least one open end. The attachment assembly further includes at least one mounting pin arranged at least partially within the at least one open end of the tubular structure and moveable along the central axis between a retracted position and an extended position. In the extended position, a portion of the at least one mounting pin protrudes for engagement with a lug and in the retracted position the at least one mounting pin is withdrawn for disengagement with the lug. The attachment assembly further includes a retraction mechanism arranged to convert a rotary input motion into linear motion of the at least one mounting pin along the central axis to drive the at least one mounting pin between the extended position and the retracted position.

Abstract: A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine, includes a blade having a vane connected to a root. A hub accommodates the root of the blade, and a ring is mounted around the root and in the hub. Stops are also mounted around the root and in the hub. A nut is threadedly engaged with a thread of the ring and is configured to bear axially against the hub to secure the assembly.

Abstract: An aircraft passenger seat unit configured for use adjacent an aisle of an aircraft cabin is disclosed. The seat unit comprises a seat, a footrest, and a movable panel. The movable panel is movable with respect to the footrest between a closed position in which the movable panel at least partially encloses a side of the footrest and an open position in which the movable panel at least partially exposes the side of the footrest such that, in use, when the panel is in the open position, a passenger can access the seat from an aisle through the partially exposed side of the footrest.

Abstract: Described herein is a privacy panel for a passenger includes a main body positioned between adjacent passenger seats and an attachment mechanism removably coupled to the main body. The attachment mechanism may include a first attachment member couplable to an armrest of the passenger seat and a second attachment member coupled to the first attachment member. The second attachment member may be attachable to a fixed location on the passenger seat for preventing rotation of the armrest.

Abstract: An assembly for a turbomachine of longitudinal axis includes a nozzle carried by an annular part which is fixed to an outer casing. The nozzle has an outer annular platform from which extends, radially outwards, a radial annular wall which carries an annular attachment tab extending longitudinally upstream from the radial annular wall. The assembly has a cooling circuit with an inner annular chamber delimited radially by the outer annular platform and the annular part and delimited downstream by the radial annular wall. An intermediate annular chamber is formed radially externally to the annular attachment tab and in fluid communication with the outer casing. Means of fluid communication between the inner annular chamber and the intermediate annular chamber is formed in the annular attachment tab of the nozzle.

Abstract: Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.

Abstract: A cam includes a cylindrical ring having a substantially circular outer section and, externally, a helical running track. The ring has a conduit that connects two ends of the external helical running track, and the conduit comprising includes a track for recirculation between the ends of the running track.

Abstract: The present invention relates to a mechanism for changing the pitch of a propeller of a turbine engine, the mechanism comprising an electrohydraulic actuator that comprises: —an electric machine comprising a rotatable actuator shaft; —a pumping assembly comprising two hydraulic axial piston pumps, each comprising: o a barrel housed in a cavity filled with hydraulic fluid; o a set of cylinders formed in the barrel, each cylinder housing a translatable piston and comprising an inlet port and a delivery port; o and an inclined plate, the plate of a first pump comprising a crescent-shaped inlet port for circulating the hydraulic fluid when the plate is rotated in a first direction, and the plate of a second pump comprising a crescent-shaped inlet port for circulating the hydraulic fluid when the plate is rotated in a second direction.

Abstract: A gripper for gripping a honeycomb-shaped part and depositing the part on a target surface includes gripping elements mounted on a support, each of the gripping elements being configured to be inserted into an internal cell of the honeycomb-shaped part. The gripping elements include a gripping surface that is laterally moveable relative to the support so as to come into contact with a side wall element of the internal cell.

Abstract: The present invention relates to blading (25, 26) for a turbomachine (10), comprising: —a blade (31) having an aerodynamic profile; —a platform (32, 33) comprising a flow-path surface (321) intended to delimit a primary flow path (21A) of the turbomachine (10), which path is intended, when the turbomachine (10) is in operation, to receive a flow that splits, upstream of the blade (31), into a suction-face flow (EE) and a pressure-face flow (EI); and —an internal canal (34) which has an intake opening (35) and an ejection opening (36), these each opening onto the flow-path surface (321) of the platform (32, 33), the ejection opening (36) opening downstream of the intake opening (35) and the intake opening (35) opening toward the pressure-face flow (EI).

Abstract: A device for actuating an aircraft undercarriage leg includes an electronic controller and an actuator. The actuator includes a three-phase electric motor connected to the electronic controller. The device is arranged to authorize gravity deployment of the aircraft undercarriage leg. The motor includes a stator having at least first and second star-coupled three-phase windings. The electronic controller includes a first control channel connected to the first three-phase winding, and a second control channel connected to the second three-phase winding. Each of the control channels includes a controller that generates a high-level control instruction, a driver that generates a low-level driver instruction from the high-level control instruction, and a braking circuit that brakes the motor during the gravity deployment of the leg by using energy produced by the motor. The device is arranged to use the control channels as a function of the availabilities of the components of each channel.

Abstract: A mold for manufacturing a turbomachine fan casing of composite material, includes a mandrel around which a fibrous preform of the fan casing is to be wound; counter-mold angular sectors assembled on the external contour of the mandrel which are intended to close the mold and to compact the fibrous preform wound on the mandrel; wherein each angular sector includes a first lateral flange positioned at the first end of the angular sectors and a second lateral flange positioned at a second end of the angular sectors, the first and second lateral flanges cooperating respectively with the second and first lateral flanges of the adjacent angular sectors. An angular sector includes a first groove formed in the first of second lateral flange, a first seal being positioned in the first groove, the first seal to be compressed between the first and second lateral flanges of two adjacent angular sectors.

Abstract: Method for monitoring the navigation of a vehicle for the implementation of a navigation maneuver: the method including the steps of: estimating a magnitude by a Kalman filter from parameters, a digital model of the vehicle in its environment, and at least one measurement made by at least one sensor and associated with an uncertainty on this measurement, the magnitude serving to implement the navigation maneuver; determining at least one partial derivative value of the magnitude with respect to the at least one measurement; obtaining at least one criticality value of the at least one measurement for the estimation, from the at least one partial derivative.