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

Abstract: Disclosed is a system for certifying a planned trajectory of an aircraft, the certification system being remote from the aircraft and including: a receiving device configured to receive the planned trajectory; a processing device including a plurality of processing modules, each processing module being configured to certify a given trajectory according to at least one certification rule specific to the processing module; a selection device configured to select one or more processing modules, which are referred to as active modules, to be used to certify the planned trajectory; a sending device configured to send a signal including a piece of certification information relating to the certification of the planned trajectory by all of the active modules.

Abstract: A method for automatically generating a sequence of Nmax instructions in assembly language, the sequence being executable error-free by a multi-core processor, the method comprising steps of: initializing registers of the processor, then selecting a first instruction of the predetermined sequence, optionally at random; and selecting an N+1th instruction among an instruction to read from a memory connected to the cores of the processor by a memory bus, an instruction to write to said memory, and a local instruction using only the registers of the processors, according to rules and to priorities between the rules, the rules using respective differences between statistical-metric values of statistical metrics of a memory access pattern of the sequence of N previous instructions having statistical-metric values, and setpoint values.

Abstract: Provided is a method for provisioning a user equipment with credentials in a private telecommunication network, the private telecommunication network comprising a credentials holder and a gNB/AMF or a eNB/MME.

Abstract: A space module designed to be deployed in space to form a space platform, the space module being formed of a predetermined number of elements all having the same flat shape in an extension plane of the corresponding element, each element being of a predetermined type, with at least one element forming a payload.

Abstract: Provided is a method for provisioning a user equipment with credentials in a private telecommunication network, the private telecommunication network comprising a credentials holder and a gNB/AMF or a eNB/MME. This includes sending from the user equipment 10 to the gNB/AMF or eNB/MME a provisioning request, establishing a PLS key between the user equipment and the gNB/AMF or eNB/MME thanks to Physical Layer Security, sending from the user equipment to the gNB/AMF or eNB/MME a message comprising data permitting to identify the user of the user equipment and/or the user equipment, the message being protected in integrity and confidentiality by the PLS key or by keys derived from the PLS key, sending from the gNB/AMF or eNB/MME to the credentials holder the data permitting to identify the user of the user equipment and/or the user equipment, and verifying at the credentials holder the data permitting to identify the user of the user equipment and/or the user equipment. Other embodiments disclosed.

Abstract: A Doppler radar with ambiguous electronic scanning, using an active antenna comprising an array of elementary transmission antennas and an array of elementary reception antennas with the same angular opening. The arrays have the same radiation plane. The transmission array is ambiguous with a number of ambiguous lobes within said angular opening of said elementary antennas greater than or equal to 2. The reception array comprises at least one ambiguous lobe within said angular opening. The arrays are arranged so that the product of the transmission and reception radiating patterns only produces a single main beam within the field defined by said angular opening. The coverage of said angular field by said radar obtainable by: forming at the transmission antenna radiating patterns that are focused within a field limited to the transmission ambiguity field; simultaneously forming several reception radiating patterns focused at reception in the ambiguous transmission directions.

Abstract: An electronic device configured to generate a flight plan for an aircraft. The device may include a display module configured for displaying two flight plans simultaneously and for each flight plan. The display may be configured for viewing, the common elements and distinct elements with regard to the other flight plan. Further, the device may include an acquisition module configured for acquiring a copy command. Additionally, the device may include a copying module configured for copying at least one of the distinct elements from one of the two flight plans to the other flight plan based on the copy command. Moreover, the device may include a processing module configured for generating a new flight plan based on the target flight plan and the distinct element or elements which were copied.

Abstract: A system for interacting at a distance with a pointer of a human-machine interface (HMI) of a viewing system of an aircraft cockpit, including three layers including an upper layer in the shape of an inverted V, which itself acts as a handrest knob, including a module, with a touch-sensitive flat surface, arranged on a front portion of the inverted V; at least one physical interactor to interact with the HMI arranged on a rear portion of the inverted V; and two lateral edges set back from the upper surface of the upper layer, each provided with at least one physical interactor.