Abstract: A three-dimensional object detection system includes a transmission device configured so as to transmit signals using a colored transmission method in a first plane, a reception device comprising at least two sensors arranged in a second plane perpendicular to the first plane, and processing means for processing the transmitted and received signals, wherein the reception device is raised with respect to the transmission device, and wherein the processing means are configured so as to detect the presence of objects: in the first plane based on the signals received from at least one of the sensors using the color of the transmitted signal, in the second plane based on the signals received from at least two of the sensors. The method for determining the presence of objects and for estimating their associated direction and distance is also provided.

Abstract: A flight management system of an aircraft includes a first non-critical or open world module for creating an enhanced enriched flight plan, the first module being configured to create the enhanced enriched flight plan iteratively by the following steps: initialisation of pseudo-constraints; and iterative enhancement of the choice of pseudo-constraints, until an objective of enhancement or of absence of enhancement with respect to the last best choice of pseudo-constraints is reached, based on at least one optimisation criterion and on at least one parameter representative of the environment of the flight of the aircraft; the second critical or flight management avionics module certified to calculate a path, comprising at least one critical computer and/or at least one critical piece of software for calculating and delivering as output a secured path, based on the enhanced enriched flight plan supplied by the first module.

Abstract: The invention relates to a method of manufacturing a device, the device comprising a superconducting zone (20) and an insulating zone (22) in an arrangement, comprising the steps of: depositing a buffer layer (12) on a portion of a substrate (10), etching the buffer layer (12) to obtain two zones (Z1, Z2), each first zone (Z1) being a zone in which the substrate (10) is covered by the buffer layer (12) and intended to form a respective superconducting zone (20), each second zone (Z2) being a zone in which the substrate (10) is exposed to form a respective insulating zone (22), and depositing a second layer (18) of superconducting material on the entire substrate portion (10), the first layer (12) being made of at least two superimposed sub-layers (14, 16).

Abstract: A method for processing a data stream from an uncertified video source, the data stream being intended to be displayed at least partially on a display screen of a cockpit of an aircraft, the display screen having predetermined dimensions and a predetermined resolution. The processing method comprises a calibration mode comprising a step wherein a window of interest is selected on the display screen of the cockpit by the pilot. The processing method further comprises a step wherein a portion of the data stream corresponding to the selected window of interest is displayed on the display screen.

Abstract: A method for encoding a digital signature of a neural network, implemented by an electronic device, the neural network being stored within a data structure including blocks of parameters. The method includes, for a current block of parameters including at least M parameters representing real numbers: an operation of acquiring a signature binary image from the digital signature including a set of bits extracted from parameters of the current block of parameters, and an operation of combining the signature binary image with a reference binary image delivering a coded binary image.

Abstract: The present invention relates to a device for amplifying a multi-wavelength laser beam, comprising: a. a first active laser medium having a front face and a rear face which is reflective, inclined with respect to each other at a first non-zero inclination, and b. a second active laser medium having a front face suitable for receiving the beam reflected by the rear face and refracted by the front face of the first active laser medium, and a reflective rear face, inclined with respect to each other at a second non-zero inclination, the first inclination, the second inclination and the orientation of the second active laser medium being such that the sub-beams of each wavelength, forming the output beam of the second active laser medium, are parallel to each other at the output of the second active laser medium.

Abstract: A method of integrity control, an allocation of virtual identifier, to each stream, only known to each transmitter or receiver, located at one end of the stream, a transmission by a transmitter at the end of a stream, of a message including the payload, the value of a counter of transmitted messages, and a transmission aggregate determined from the virtual identifier known to the transmitter, the value, the payload, the reception by a receiver, at the other end of the stream, of the message, and determination of a reception aggregate from the virtual identifier known to the receiver, the value received, the payload received, the end-to-end integrity check by comparing transmission and reception aggregates.

Abstract: The present invention relates to a device for amplifying a multi-wavelength laser beam, comprising: a. An active laser medium having a front face suitable for receiving the beam to be amplified each time the same passes through the active laser medium, and a reflective rear face inclined with respect to the front face, the beam reflected by the rear face and refracted by the front face during the n-th pass being called the n-th useful beam, and b. a first optical return unit arranged along the path of the first useful beam and configured for returning the first useful beam on the front face for a second pass through the active laser medium so that the sub-beams of each wavelength, forming the second useful beam, are parallel to each other at the end of the second pass.

Abstract: The present invention relates to a device (16) for determining the attitude of a carrier comprising a GNSS receiver apt to receive GNSS signals from one or a plurality of antennas (14) arranged in known positions; the determination device (16) comprising: a movement generation module (22) configured for generating a movement of an apparent phase center according to a control law; a control module (23) configured for determining the control law; a determination module (24) configured for determining an absolute orientation of a vector of interest from at least one observable value supplied by the GNSS receiver (12) and from the control law, and for determining at least one component of the attitude of the carrier from the absolute orientation of the vector of interest.

Abstract: The invention relates to a radar system comprising: a frequency synthesizer, configured to generate a modulated local signal (Sf0+?f0); at least one frequency multiplier, configured to supply an intermediate-frequency local signal (Sf_inter+?f_inter) to each emission channel (8) and to each reception channel, the intermediate-frequency local signal (Sf_inter+?f_inter) being a fractional multiple of the modulated local signal (Sf0+?f0); a plurality of emission frequency transposition components, the emission frequency transposition components being synchronized with one another by the modulated local wave (Sf0+?f0); a plurality of reception frequency transposition components, the reception frequency transposition components being synchronized with one another by the modulated local signal (Sf0+?f0), the reception channels being configured to demodulate the intermediate-frequency reception signal (Sf_inter_Rx+?f_inter_Rx) using the intermediate-frequency local signal (Sf_inter+?f_inter).

Abstract: The present method includes a first step of obtaining first values of compensation coefficients for magnetic anomalies of the magnetometer, and a second step of in-flight refining including: a) an acquisition of a plurality of magnetic field vector values and associated aircraft attitude angle values; b) a calculation of a magnetic heading as a function of the first values of the compensation coefficients and values of magnetic field vector; c) a recursive calculation of a slope coefficient, as a function of a difference in heading between the calculated magnetic heading and a reference magnetic heading, and of values for aircraft attitude angles; and d) a calculation of a value of compensation coefficient for vertical magnetic anomalies using a vertical bias estimator as a function of the slope coefficient, aircraft attitude angle values, and local terrestrial magnetic field values.

Abstract: A mechanical flight control actuator, intended to provide assistance for piloting an aircraft, includes a first electric motor, a second electric motor and a backup assist shaft. The backup assist shaft is adapted to be set into rotation by the second electric motor. The backup assist shaft includes a backup assist clutch device, the backup assist clutch device being capable of assuming an active position, wherein the backup assist shaft drives the output shaft, and an inactive position, and the backup assist clutch device is in its active position when the input clutch device is in its inactive position and the backup assist clutch device is in its inactive position when the input clutch device is in its active position.

Abstract: A dual-band analogue filter that is passing for IFF signals and ADS-B signals in a first and a second frequency band, and to reject signals received outside these bands, implemented using multi-planar technology, and comprising, in succession: a layer comprising an input port and an output port, a layer comprising a ground plane having openings facing the input port and the output port, a layer comprising N band-pass resonators, a layer comprising N band-stop resonators, arranged such that: the band-pass resonators are connected in pairs by coupling, the first and the last band-pass resonator are connected to the input port and the output port by electromagnetic coupling, each band-pass resonator is connected to a band-stop resonator by electromagnetic coupling.

Abstract: A localization method, implemented in a satellite system includes at least a first constellation associated with a probability of occurrence of multiple failures lower than a given integrity risk, where the method may advantageously comprise the following steps implemented by a radioelectric device: receive a plurality of navigation signals; select failure modes to be monitored other than the multiple failures of the first constellation; determine a navigation solution and a plurality of navigation sub-solutions; calculate, for each navigation sub-solution, one or more corresponding detection thresholds; calculate one or more protection levels.

Abstract: A method of generating a peripheral image of an aircraft having pixels obtained from a plurality of cameras equipping the aircraft. The method is implemented by an electronic generation device. The method comprises a step of receiving a position of a peripheral point of view from which the peripheral image is to be generated. The method comprises steps of obtaining an orientation of the aircraft and of acquisition of a respective image from each camera. The method comprises a step of calculating a respective transfer function for each camera, each transfer function being intended for being applied to a pixel of the peripheral image so as to identify a possible corresponding pixel of the acquired image associated with the transfer function. The method comprises a step of generating the peripheral image from the images acquired from each camera and from each calculated transfer function.

Abstract: An aerodynamic measurement probe intended to measure a local angle of attack of an airflow circulating along the fuselage of an aircraft, the support comprising a circular cover with a central opening which is passed through by the mobile shaft, the outer surface of the cover comprising a frustoconical face exhibiting symmetry of revolution about the longitudinal axis, the cover comprising polyether ether ketone reinforced with glass or carbon fibers, with a thermal conductivity of less than 3 W·m?1·K?1 and being provided with metallic inserts at its fastenings, at least one metallic electrical continuity insert being configured to establish an electrical connection between the inner part of the probe and an interface of the metallic insert disposed under the lower periphery of that part of the metallic insert which is furthest away from the shaft.

Abstract: This angle-of-attack sensor, in particular for an aircraft, of the type including a sensor body (11) on which a wind vane (12) is mounted movable in rotation by a flow, is characterized in that the wind vane (12) includes at least one deflector (13, 14) extending from the leading edge of this wind vane over at least part of the intrados and/or extrados thereof.

Abstract: A navigation and positioning device including at least an inertial measurement unit, a GNSS measurement receiver, a unit for modeling the displacement(s) of the vehicle, a main Kalman filter calculating navigation data corrections by data hybridization, and at the output of the main Kalman filter at least two distinct Kalman sub-filters including a first Kalman sub-filter calculating navigation data corrections by hybridization of data provided by the inertial measurement unit and by the receiver of GNSS satellite positioning measurements, and a second Kalman sub-filter calculating navigation data corrections by hybridization of data provided by the inertial measurement unit and by the unit for modeling displacement(s) of the vehicle.

Abstract: A quasi-optical beamformer includes a plurality N>1 of power feeds (PF), each of the i?[1; N] power feeds (PF) being configured to emit a respective radio-frequency beam denoted Ri, a radio-frequency transmission line (LT) fed at a first end by the power feeds and comprising at a second end a plurality of network ports (PR) that are configured to collect radio-frequency radiation, the transmission line (LT) comprising a radio-frequency waveguide (GO) that comprises at least two metal plates (PM) that are stacked so as to guide the radio-frequency beams Ri, i?[1; N] towards the network ports (PR), the transmission line (LT) extending along a central main axis denoted axis x, a first reflector (M1) having a first centre (C1) centred on the axis x and a first effective radius of curvature and being configured to reflect the guided radio-frequency beams Ri, i?[1; N], a second reflector (M2) having a second effective radius of curvature and being configured to reflect the radio-frequency beams (RFi) reflected b

Abstract: A method for characterizing cutaneous pigmentary disorders in an individual which includes: for each pigmentary disorder: on a date tkm acquiring 2D images of a pigmentary disorder from a plurality of angles and reconstructing at least one 3D image; storing the images in a first folder; on the basis of the images, calculating parameters of the pigmentary disorder, and storing in a second folder; evaluating the parameters and storing in a third folder; iterating at least one of the four preceding steps on multiple dates, and for each iteration: comparing the data for at least one period and identifying the changes; storing in a fourth folder per period; for each fourth folder, grouping the folders together in a fifth folder defining a snapshot of the pigmentary disorder; aggregating the fifth folders in a sixth folder defining a dynamic profile of the pigmentary disorder; iterating the preceding steps to obtain a sixth folder for each additional pigmentary disorder; and generating, for the individual, a knowle