Abstract: The invention relates to a method for processing a radio navigation signal originating from a satellite (SAT) and received by a radio navigation receiver comprising a plurality of receive antennas, each antenna being configured to receive signals originating from a satellite of interest (SAT), from at least one jammer and possibly from at least one other satellite (SAT?) in given directions, the method comprising the following steps: detecting (E1), on the basis of the signal received by each antenna, at least one direction of a jamming signal; attenuating (E2, E2?) the detected jamming signal in the detected direction; in which method detecting (E1) the direction of a jamming signal is based on determining a covariance matrix dependent on the signals received by each antenna given by (i), where Z is a matrix of size N×M in which each column corresponds to the signal received by each antenna, N denoting the number of samples acquired during a fixed period ?T and M being the number of antennas.

Abstract: A measuring device has a magnetic circuit with a first and second armature elements that are positioned one on either side of an axis X and are manufactured with at least one ferromagnetic material. A magnet is situated between the armature elements such that a first pole of the magnet is positioned next to the first armature element and such that a second pole of the magnet is positioned next to the second armature element. A rod is arranged to be secured to a target and inserted between the armature elements to slide along the axis X. The rod has a variable section along its length such that a magnetic flux in the magnetic circuit depends on a linear position of the rod along the axis X. At least one sensor is arranged to measure the magnetic flux, which corresponds to the linear position of the target.

Abstract: A method comprising steps of: performing spatial filtering (104, 204) causing an attenuation of power of radio signals received by an antenna system in an angular sector (A); detecting (106, 206, 210) that a radio signal is received by the antenna system while the angular sector (A) includes a direction pointing at a satellite (S1) forming part of a constellation of positioning satellites, that the received radio signal is not subject to the attenuation caused by the spatial filtering, and that the received radio signal is in the form of a positioning signal emanating from the satellite (S1); and, following the detection, implementing processing (112, 114, 212, 214) under the assumption that the antenna system has fallen victim to decoying.

Abstract: A device comprising: a stand; a frame rotatably mounted relative to the stand; a control arm rotatably mounted on the frame; a roll spider rotatably mounted on the frame; a pitch spider rotatably mounted on the control arm; a roll motor that is stationary relative to the frame and that includes a roll pin rotatably mounted on the roll spider; and a pitch motor that is stationary relative to the frame and that includes a pitch pin rotatably mounted on the pitch spider. A rotary connection device.

Abstract: A method and a system for transmitting data in a carrier sense multiple access wireless network wherein a plurality of data transmission devices send respectively at least one data frame at different moments from each other. Each transmission device, when it is initialised: loads the final value of a first, second and third counter, triggers the second counter as from its initial value, triggers, when the second counter has arrived at its final value, the first, triggers, when the first counter has arrived at its final value, the third counter, which is reinitialised to its initial value and retriggered whenever the presence of data is detected on the radio medium, transfers at least one data frame when the third counter has arrived at its final value.

Abstract: A system couples a driving shaft and a driven shaft in rotation and without play. The driving shaft includes a tubular end with at least one internal longitudinal groove receiving the driven shaft and having at its end a projecting cylindrical transverse pin configured to engage in the groove. A return spring for the pin urges the pin without play against a longitudinal edge of the groove. The spring includes a first helical section for fastening to the driven shaft and threaded by screwing through the pin. A second section of the spring bears on the pin, and a third elastic return section of the spring acts elastically on the second section.

Abstract: A method includes for each of the portions of a guide of the actuator, obtaining an operating signal measured when a movable element of the actuator travels over the guide portion in question, upon each of a plurality of successive activations of the actuator; for each of the guide portions, seeking wear of the actuator from the operating signals obtained for this guide portion; and locating the wear on the guide or on the motor according to the guide portions from which the wear has been found.

Abstract: The invention relates to a method for communicating data between communication equipments, where the first communication equipment (EqptN) is put into the emission mode (Xmit) for the frame (TrN) containing its identification (D_PID), while each second communication equipment (Eqpt1, EqptN+1, EqptN+x) is put into the receiving mode (Rcv), then the equipment (EqptN) is put into the receiving mode (Rcv), each equipment (Eqpt1, EqptN+1, EqptN+x) prescribes its local emission window (Ftle1, FtleN+1, FtleN+x), which is associated with its identification, during which it is put into the emission mode (Xmit) for its frame, a time of beginning (IDF1, IDFN+1, IDFN+X) of the window being a determined function, increasing with respect to a difference equal to its identification from which the identification (D_PID) is subtracted, each equipment is put into the emission mode, during which it emits its frame containing its identification during its window starting at the beginning time.

Abstract: A system for recharging an autonomous aerial vehicle includes a base, a supply boom, a receiving basket, a centering device, and a locking device. The supply boom includes a tip and first recharger. The receiving basket has an inner wall delimiting a cavity that may receive the tip of the supply boom. The receiving basket including a second recharger that is complementary to the first recharger. One of the supply boom and the receiving basket is mounted on the autonomous aerial vehicle while the other is mounted on the base. The centering device centers the tip of the supply boom in the cavity of the receiving basket. The locking device is controlled by a controller and locks the supply boom in the receiving basket.

Abstract: Rudder pedal and brake inceptor devices are described that utilize a straight-line mechanism and rotary joints to achieve straight line motion in a compact volume. The devices can include four or more bar linkages that translate forward motion of a pedal into a rotary motion of a common shaft, such that forward motion of one pedal causes the other pedal to retract while allowing for yaw motion control of the aircraft.

Abstract: An electrical conversion system includes an inverter arranged according to a multilevel type topology with k arms and a command device for cut-off against an electrical overload, connected to a set of first intermediate lines to measure a first intermediate continuous voltage. The cut-off command device is configured to determine a fault by detecting if the first measured intermediate continuous voltage is outside of a nominal voltage variation range [Vmax1, Vmin1] of the first intermediate voltage and to transmit a generalised opening command signal for an opening of the electronic commutation switches of each arm when the fault is determined.

Abstract: An aircraft seat includes an actuator and a movement transmission device. The movement transmission device includes a frame having at least one bearing face and one braking face; a drive body configured to being rotated relative to the frame, the drive body having a bearing face and a braking face; and an elastic element suitable for keeping the braking face of the drive body at a defined distance from the braking face of the frame, the elastic element having a determined stiffness and being prestressed such that, when an axial load greater than a threshold load is applied to the drive body, the braking face of the drive body comes into contact with the at least one braking face of the frame.

Abstract: An alternative piloting system arranged to be integrated in a pre-existing aircraft that includes original systems having flight control and autopilot systems.

Abstract: Disclosed is an aircraft provided with a light signaling system including at least one light-emitting device at the tip of each wing and at least one light-emitting device at the tip of the tail. Each light-emitting device at the wingtip can be arranged in a recess formed in the profile of the wing and include a covering At least one light source and a protective glass can be arranged on the recess so that the outer surface matches the shape of the wing. The inner surface of the protective glass can be provided with at least one local variation in thickness so as to increase the angular aperture of each wingtip light-emitting device in order to ensure the overlap between the light-emitting devices at the wingtip and the light emitted by the light-emitting device on the tail.

Abstract: A variable inductive displacement sensor includes a primary excitation coil, a first secondary coil, and a second secondary coil. The primary excitation coil is configured to generate a variable magnetic field, and the first and second secondary coils are configured to each generate a signal induced by the variable magnetic field. The primary coil and the first and second secondary coils each have one end which is intended to be connected to a common ground.

Abstract: The invention relates to a force application device for an aircraft control column, the control column comprising a control lever configured to rotate a first shaft and a second shaft, the force application device comprising a first force feedback member configured to exert a resistive force opposing the rotation of the first shaft, a second force feedback member configured to exert a resistive force opposing the rotation of the second shaft and a common braking device comprising a housing, a first braking member and a second braking member which are coaxial and mounted rotatably inside the housing and configured to engage with the first shaft and the second shaft, respectively, so as to brake them, preferably simultaneously.

Abstract: This system (36) for controlling an aircraft thrust reversal means comprises a reverse idle control means (38), a first detection means (31) configured to detect, when the reverse idle control is active, a condition for activation of the thrust reversal means, and an actuation means (52) configured to activate the thrust reversal means when the first detection means (31) detects a condition for activation of the thrust reversal means. It further comprises a second detection means (42, 44, 46, 48, 49) configured to detect a condition for activation of the reverse idle control, the control means (38) being configured to activate the reverse idle control when the second detection means (42, 44, 46, 48, 49) detects a condition for activating the reverse idle control.

Abstract: A method for monitoring an aircraft landing gear. The method includes using information from at least one accelerometer firmly secured to a landing gear wheel mounted to rotate on a landing gear axle to estimate an angle of deflection ? of the axle at least when the wheel is in contact with the ground.

Abstract: A method for dating images obtained by at least one camera equipping a vehicle includes acquiring a reference signal including time information and generating a modulated signal in response to the reference signal. The modulated signal has at least one retiming pulse with a retiming period which that is different from a base period of the modulated signal. The method further includes, for each camera, acquiring images at a frequency depending on the frequency of the modulated signal, each image being associated with a timestamp provided by the camera, and determining the time difference between the timestamps of two successive images of the camera. If the time difference determined between said timestamps is different from the base period of the modulated signal, the method assigns a reference date to said images depending on the time information of the reference signal.

Abstract: A multispectral filter with a filtering array for a sensor with an array of elementary sensors, said filtering array comprising an elementary pattern formed of an arrangement of N elementary cells capable of filtering central wavelengths ?1, . . . , ?k, . . . , ?N, the position of the central wavelengths in the elementary pattern being determined so that: each wavelength being associated with an integer e1, . . . , ek, . . . , eN, selected so that each of the products e1x ?1, . . . , ekx ?k, . . . , eNx ?N is substantially constant, each central wavelength ?k is positioned at ek positions in the elementary pattern so that the maximum ratio between the distance between two proximal positions of said central wavelength and the associated central wavelength is minimal.