Abstract: The disclosure relates to a housing comprising at least one composite wall comprising woven or braided carbon fibers covered with a thermoplastic or thermosetting resin, an electronic card carrying electronic components, and a heat transfer device having at least one portion facing an electronic component to be cooled of the electronic card, said heat transfer device being inserted inside the composite wall, the heat transfer device comprising at least one cooling conduit containing a cooling fluid.

Abstract: The invention relates to a method for locating a target by means of a detecting device comprising a photodetector comprising N×M quadrants positioned with respect to a sighting axis of the detecting device, the photodetector being configured to detect optical signals from the target to be detected, said method being implemented in a processing unit of said device and comprising the following steps, the target scattering an optical signal: —acquiring the signals detected by each quadrant, which correspond to the signals scattered by the target toward the quadrants; —processing the acquired signals to determine an elevation angle error and an azimuth angle error of the direction of the target with respect to the sighting axis of the device; —processing the acquired signals with a view to deducing therefrom indicators of the distribution of the signals detected by the quadrants; —processing the determined elevation angle error and azimuth angle error with a view to deducing therefrom indicators of the theoretica

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 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: 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: 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: 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: The present invention relates to a bidirectional data communication method for a bidirectional data communication system (100), in particular an embedded bidirectional data communication system (100), comprising: at least one first communicating device (200a) configured to implement a single-pair Ethernet protocol and one second communicating device (200b) configured to implement a single-pair Ethernet protocol and comprising a second packet management module (220b) connected to a first physical link management module (231b) and to a second physical link managment module.

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: A method for controlling an engine, a device for controlling an engine and an aircraft, the method comprising the steps of determining a first intensity Kp, representing a stiffness, according to a physical stiffness Kss of the mechanical connection and a stiffness setpoint Kpspec to be rendered on the control column, a second intensity Kv, representing a damping, according to a physical damping fss between the control column and the engine and a damping setpoint Kvspec to be rendered on the control column, and a third intensity Ka, representing an inertia, according to a physical inertia Jss of the control column and an inertia setpoint Kaspec to be rendered on the control column.

Abstract: A tactile interface including a touch pad and a support, the touch pad being hingedly attached to the support between the extended active position and a retracted inactive position, in which the pad is folded back towards the support wherein the support constitutes a drawer which is movable in a casing between a pulled-out position in which the interface is in the active position and an inserted position in which the interface is in the retracted position.

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 method for navigating a carrier using a Kalman filter estimating a navigation state of a carrier, comprising: obtaining, from a signal transmitted by the satellite and subsequently received by the carrier, a delta range measured between the carrier and a satellite and another measured kinematic datum which is associated with the satellite, generating, from position data for the carrier and the satellite in the navigation state, an estimated delta range between the carrier and the satellite, calculating, using the delta ranges, a delta range innovation associated with the satellite, carrying out a test on the delta range innovation, the test result indicating whether or not the signal was a multi-path signal, using, by means of the filter, the kinematic datum as an observation to update the navigation state provided that the test result indicates that the signal was not a multi-path signal.

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: An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.

Abstract: A shielding element comprises a rigid substrate and at least one electrically conductive two-dimensional structure which is placed on one of the faces of the substrate. The substrate and the electrically conductive two-dimensional structure are such that the shielding element has optical-transmission and shielding-efficiency values at least one of which varies between two zones of the shielding element. Such a shielding element enables easier assembly of a detection system comprising multiple optical sensors.

Abstract: A method of detecting blocking of a rotor of a motor driving an actuator member with movement in translation between a first abutment and a second abutment, the method comprising the steps of, during an angular movement of the rotor, estimating at least a position (X) of the actuator member relative to the two abutments, a travel direction of the actuator member relative to the two abutments, and also a travel speed (V) of the actuator member; and on the basis at least of the estimated position of the actuator member, of the estimated travel direction of the actuator member, and of the estimated travel speed of the actuator member, detecting blocking of the rotor.

Abstract: A telescope including a fastener plate, a primary mirror carried by a front face of the plate, and a secondary mirror held facing the primary mirror by a support. The primary mirror is connected to the plate by fastener elements each having a bearing receiving a pin as a sliding fit, the pin being adhesively bonded in the bearing by means of a structural adhesive; and in that the pin is provided with a central channel having a first end opening out into a portion of the pin that is accessible when the pin is in position in the holes in order to receive one end of a cannula for injecting adhesive, and a second end opening out at least into a transverse channel having at least one end opening out into the bearing.

Abstract: A device for acquiring signals from a sensor, the device comprising a differential amplifier, two bias resistors for biasing of the measurement device, a common mode and differential mode filter circuit, and two lightning limiter components. The differential amplifier is of the high common mode range type, the limiter components are dimensioned to reduce a lightning voltage to a maximum voltage value of the order of about one hundred volts and the filter circuit and the bias resistors are dimensioned to withstand that maximum voltage value. A correspond method for protecting a device against lightning.

Abstract: An electromechanical device for actuating a movable flight control surface having a skin hinged to a structure of an aircraft about a pivot axis, the device including: at least two electric motors for causing the skin to pivot about the pivot axis; a power circuit and a control circuit for powering and controlling each of the motors; and a device for limiting opposing forces exerted by the two electric motors.