A circuit can be configured to operate as a dual-trip point data slicer for serial demodulation. The circuit can include an input port configured to receive an input signal. The circuit can further include a first output port electrically coupled to the input port by a first circuit path. The circuit can further include the first circuit path, which can be configured to provide the input signal from the input port to the first output port. The circuit can further include a second output port electrically coupled to the input port by a second circuit path that is parallel to the first circuit path. The circuit can further include the second circuit path, which can be configured to provide a reference signal to the second output port. The reference signal can be based on a delayed version of the input signal.
A spacecraft for the distribution of electrical energy to client craft at points situated in free space, in orbit and/or on a celestial body includes a main structure equipped with an electric thruster, with a chemical thruster and with a solar generator, a first fuel container for fuel intended for the electric thruster, and a second fuel container for fuel intended for the chemical thruster. The spacecraft is able to be modulated such that the main structure can be coupled/decoupled alternatively to/from the first container or the second container, the first container and the second container are able to be coupled/decoupled to/from one another, and the solar generator can be deployed or retracted.
B64G 1/40 - Aménagements ou adaptations des systèmes de propulsion
B64G 1/62 - Systèmes de retour sur terre; Dispositifs de freinage ou d'atterrissage
B64G 1/64 - Systèmes pour réunir ou séparer des véhicules spatiaux ou des parties de ceux-ci, p.ex. aménagement pour l'accostage ou l'amarrage
3.
Electronic device for storing a terrain database, method for generating such a database, related avionics system, monitoring method and computer programs
This electronic device for storing a terrain database for an avionics system is carried on board an aircraft. The terrain database corresponds to a terrain zone likely to be overflown by the aircraft, represented in the form of a surface area divided into meshes, each mesh corresponding to a sector of the terrain zone, the terrain database having a first resolution and comprising first terrain elevation values, each associated with a respective mesh. The terrain database further comprises, for each mesh, an uncertainty value associated with the respective first elevation value, at least one uncertainty value being calculated from a plurality of second terrain elevation values associated with said mesh and from a second terrain database having a second resolution higher than the first resolution.
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.
G01S 19/55 - Résolution de l'ambiguïté de la phase de la porteuse; Ambiguïté flottante; Procédé LAMBDA [compensation par les moindres carrés de la décorrélation de l'ambiguïté]
G01S 19/36 - Récepteurs - Détails de construction ou détails de matériel ou de logiciel de la chaîne de traitement des signaux concernant l'étage d'entrée du récepteur
5.
Avionic calculator comprising a multicore processor, with a filtering core between open and avionic domains
The avionic calculator is suitable for being carried on-board an aircraft and comprises a multi-core processor configured for executing avionic software applications. The processor includes at least one primary core for communicating with at least one avionic equipment distinct from the calculator, each avionic equipment being carried on-board the aircraft and belonging to an avionic domain; at least one secondary core for communicating with at least one electronic device external to the avionic domain; and a tertiary core for performing at least one filtering of a data message received from a respective device external to the avionic domain and intended for a respective avionic equipment of the avionic domain. Each avionic software application being executable by the at least one primary core or the at least one secondary core.
Commissariat à l'énergie atomique et aux énergies alternatives (France)
THALES (France)
Centre national de la recherche scientifique (France)
UNIVERSITE GRENOBLE ALPES (France)
Inventeur(s)
Attane, Jean-Philippe
Vila, Laurent
Bibes, Manuel
Abrégé
A device for modifying at least the direction of magnetization of a magnetic layer, the modifying device including a ferroelectric layer having a ferroelectric polarization, arranged on or under the magnetic layer so as to define a stack including at least the magnetic layer and the ferroelectric layer, a generator apt to inject an electric current into the stack along a direction parallel to the plane of the layers of the stack, and a modification unit apt to modify the ferroelectric polarization of the ferroelectric layer, for modifying, with the generator, the direction of magnetization of the magnetic layer.
G11C 11/16 - Mémoires numériques caractérisées par l'utilisation d'éléments d'emmagasinage électriques ou magnétiques particuliers; Eléments d'emmagasinage correspondants utilisant des éléments magnétiques utilisant des éléments dans lesquels l'effet d'emmagasinage est basé sur l'effet de spin
G11C 19/08 - Mémoires numériques dans lesquelles l'information est déplacée par échelons, p.ex. registres à décalage utilisant des éléments magnétiques utilisant des couches minces dans une structure plane
The present invention relates to a method for determining positions by an optronic system in a scene, the scene comprising reference elements of known geographic coordinates, the optronic system comprising the following elements integrated into said optronic system:
a. a digital imager,
b. a memory wherein is stored, for each reference element of the scene, an indicator representative of said point associated with the geographic coordinates of said point,
c. a display element that displays the indicators stored in the memory,
d. a measurement module comprising at least one element chosen from among: a compass, a goniometer and a telemeter,
e. a calculation unit,
the method being implemented by the elements integrated in the optronic system.
A method for selecting at least one satellite navigation service provider from a plurality of predetermined providers, the selection method being computer-implemented and comprising: a step for receiving a geographical position; a step of determining an indication relating to the authorization of use of at least one provider of the plurality of predetermined providers, the determining step being implemented by at least one artificial neural network (24) associated with said provider, an input variable of the artificial neural network (24) being the geographical position, an output variable of the artificial neural network (24) being said indication; a step for selecting at least one provider for satellite navigation of an aircraft.
G01S 19/07 - Systèmes de positionnement par satellite à radiophares émettant des messages horodatés, p.ex. GPS [Système de positionnement global], GLONASS [Système global de navigation par satellite] ou GALILEO Éléments coopérants; Interaction ou communication entre les différents éléments coopérants ou entre les éléments coopérants et les récepteurs fournissant des données pour corriger les données de positionnement mesurées, p.ex. DGPS [GPS différentiel] ou corrections ionosphériques
9.
OMNIDIRECTIONAL OPTRONIC SYSTEM HAVING TWO ROTATION AXES
An omnidirectional optronic system includes two axes of rotation, a carrier axis and a carried axis, that are perpendicular to each other, for an aircraft targeting pod, having an imaging channel and a laser channel, the laser channel at the point of injection at the entrance of the system and the imaging channel being concentric with the carrier axis, then split and emitted out in parallel.
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
Inventeur(s)
Delga, Alexandre
Espiau De Lamaestre, Roch
Abrégé
An optoelectronic device includes at least one pixel, each pixel comprising an optical resonator comprising a photodetecting structure confined between a reflective metal layer and a second reflective metal layer; and a readout integrated circuit arranged on a substrate and comprising at least one buried readout electrode dedicated to the pixel and at least one metal or dielectric outer layer. The assembly comprising at least the reflective metal layer and the outer layer of the readout integrated circuit is called a planar assembly structure. The first metal layer is connected to the readout electrode by way of a metal via passing through the optical resonator structure and the planar assembly structure. The metal via is electrically isolated from the photodetecting structure and from the planar assembly structure.
A method and device generate the path of a moving apparatus, within a predetermined time constraint, between a start and end points, the moving apparatus having predetermined movement constraints. The method includes: calculating a grid of a movement area of the mobile device, the start point and the end point belonging to the movement area, the grid being formed by a set of adjacent grid elements; calculating a cost map associating at least one cost value with each grid element; calculating, by a wavefront propagation method using the grid and the calculated cost map, a first integrated cost map associated with the point of departure and a second integrated cost map associated with the point of arrival; and determining a diverted path linking the points of departure and arrival via a detour point, using the first and second integrated cost maps.
G01C 21/20 - Instruments pour effectuer des calculs de navigation
12.
METHOD FOR CONTROLLING A SET OF COMPUTER BOARDS OF A MEDIA SERVER ON-BOARD AN AIRCRAFT, ASSOCIATED COMPUTER PROGRAM, ELECTRONIC CONTROL DEVICE AND MEDIA SERVER
The invention relates to a method for controlling a set of computer boards of a media server intended for be carried on-board an aircraft. Each computer board is intended for executing at least one software function. The method is implemented by an electronic control device and comprises a step 200 of selection of a computer board from among the set of computer boards, a first step 220 of managing a reassignment, to one or a plurality of computer boards other than the selected board, of one or each software function pending execution by the selected board, and, following the first management step 220, a step of sending 230 a restart instruction to the selected board.
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
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.
H01S 3/00 - Lasers, c. à d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet
H01S 3/02 - Lasers, c. à d. dispositifs utilisant l'émission stimulée de rayonnement électromagnétique dans la gamme de l’infrarouge, du visible ou de l’ultraviolet - Détails de structure
H01S 3/23 - Agencement de plusieurs lasers non prévu dans les groupes , p.ex. agencement en série de deux milieux actifs séparés
14.
SYSTEM AND METHOD FOR TREATING MATERIAL BY LASER SHOCK UNDER CONFINEMENT IN A LIQUID
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventeur(s)
Rondepierre, Alexandre
Rouchausse, Yann
Berthe, Laurent
Abrégé
A system for treating a target by laser shock in a regime of confinement in a liquid, the system includes a pulsed laser generating a beam having a pulse duration of between 1 ns and 30 ns and a wavelength, a concentrating optical device having a focal length and configured to concentrate the beam on the surface of the target, the incident laser beam on the concentrating device having a diameter, a tank filled with the liquid having a refractive index n, a desired value of the diameter of the beam on a surface of the target being predetermined and named Dst, a thickness of liquid passed through by the beam before reaching the surface of the target being chosen such that a laser intensity on the surface of the liquid (Isl) is less than or equal to a laser intensity on the surface of the target (Ist) divided by 2.
B23K 26/122 - Travail par rayon laser, p.ex. soudage, découpage ou perçage sous atmosphère particulière, p.ex. dans une enceinte dans un liquide, p.ex. sous l’eau
B23K 26/356 - Travail par rayon laser, p.ex. soudage, découpage ou perçage pour le traitement de surface par traitement par choc
B23K 26/0622 - Mise en forme du faisceau laser, p.ex. à l’aide de masques ou de foyers multiples par commande directe du faisceau laser par impulsions de mise en forme
B23K 26/064 - Mise en forme du faisceau laser, p.ex. à l’aide de masques ou de foyers multiples au moyen d'éléments optiques, p.ex lentilles, miroirs ou prismes
15.
SATELLITE SYSTEM AND METHOD FOR GEOLOCATING A RADIOFREQUENCY TRANSMITTER
A satellite configured to operate radiofrequency communications from one or more antenna systems. The satellite further comprises a device dedicated to locating RF equipments comprising: a reception antenna comprising a plurality N of radiating elements configured to receive an RF signal, analogue means for frequency multiplexing the signals received on the N radiating elements, means for transmitting the multiplexed signals to a satellite station on the ground. A complete satellite system further comprising a satellite station and computation means configured to receive the multiplexed signals, demultiplex them and implement goniometry processing operations to determine the position of the RF equipment to be located, and to the associated locating method.
A consolidation method implementing: a first sensor able to determine a computed position {circumflex over (x)}(1) of the aircraft, a characterization of the positioning error and a horizontal protection level HPL(1), a second sensor, with a different design and with a design level equivalent to the first sensor, able to determine a second position {circumflex over (x)}(2) of the aircraft and a characterization of the positioning error of the second position {circumflex over (x)}(2), and comprising the steps: a. estimating a horizontal deviation between the computed position {circumflex over (x)}(1) and the second position {circumflex over (x)}(2), b. comparing the horizontal deviation with a detection threshold, c. if the horizontal deviation is below the detection threshold, computing an additional horizontal protection level HPL(MON) of the computed position {circumflex over (x)}(1), d. estimating a consolidated horizontal protection level HPL(CON), e. comparing the consolidated horizontal protection level HPL(CON) and a horizontal alert limit HAL, f. if the consolidated horizontal protection level HPL(CON) is less than the horizontal alert limit HAL, horizontally confirming the computed position {circumflex over (x)}(1).
The present invention relates to night-vision binoculars, comprising:
a. a fixed lens assembly comprising a projection lens having an output axis referred to as the projection axis,
b. two eyepieces, each eyepiece having an output axis referred to as the vision axis, the vision axes of the two eyepieces being parallel and separated by an adjustable distance, called inter-pupillary distance, the vision axis of each eyepiece also being parallel to the projection axis of the lens assembly and having the same non-zero centre-to-centre distance from the projection axis of the lens assembly, each eyepiece being rotatably movable relative to the projection axis of the lens assembly so as to adjust the inter-pupillary distance.
G02B 23/12 - Télescopes ou lunettes d'approche, p.ex. jumelles; Périscopes; Instruments pour voir à l'intérieur de corps creux; Viseurs; Pointage optique ou appareils de visée avec des moyens pour renverser ou intensifier l'image
G02B 7/12 - Réglage de la distance pupillaire de jumelles binoculaires
G02B 27/14 - Systèmes divisant ou combinant des faisceaux fonctionnant uniquement par réflexion
A method and device for assisting a pilot in flight management is provided, by enabling the pilot to anticipate situations involving a risk of collision with another aircraft or with the ground, or to anticipate a risk of deviation from a flight path.
The monitoring system (1) is used for detecting an incapacitation of the pilot of an aircraft, said aircraft being equipped with a piloting device (40) which can be actuated manually by the pilot. Same includes: at least one pressure sensor integrating a contact sensor (11, 12) mounted on the surface of the piloting device (40), so as to generate an elementary indicator when a pressure exerted by the pilot on the piloting device is adapted to the use of the piloting device; and a computing unit (2) programmed for processing the elementary indicator delivered by the pressure sensor and for determining a current state of the pilot and, when said current state corresponds to an incapacitation of the pilot, for issuing an alarm.
In the field of air navigation, a computer-implemented method includes loading an initial active flight plan for an aircraft comprising a first approach procedure to a runway up to a missed approach point ending between the missed approach point and a final point; loading a secondary flight plan comprising an approach procedure to the runway between the missed approach point and the runway, and a second missed approach procedure at the end of the approach, and ending at a second final point; receiving an instruction from an operator of the aircraft to link the initial active flight plan and the secondary flight plan; in the event of a go-around by the operator at the latest at the missed approach point, activating the missed approach procedure; otherwise, automatically selecting the secondary flight plan as active flight plan and activating the second approach.
G08G 5/02 - Aides pour l'atterrissage automatique, c. à d. systèmes dans lesquels les données des vols d'avions arrivant sont traitées de façon à fournir les données d'atterrissage
21.
METHOD AND SYSTEM FOR LOCALIZING RADIO EQUIPMENT USING AT LEAST TWO SATELLITE CONSTELLATIONS
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.
The invention relates to a radar system comprising:
a frequency synthesizer, configured to generate a modulated local signal (Sf0+Δf0);
at least one frequency multiplier, configured to supply an intermediate-frequency local signal (Sf_inter+Δf_inter) to each emission channel (8) and to each reception channel, the intermediate-frequency local signal (Sf_inter+Δf_inter) being a fractional multiple of the modulated local signal (Sf0+Δf0);
a plurality of emission frequency transposition components, the emission frequency transposition components being synchronized with one another by the modulated local wave (Sf0+Δf0);
a plurality of reception frequency transposition components, the reception frequency transposition components being synchronized with one another by the modulated local signal (Sf0+Δf0), the reception channels being configured to demodulate the intermediate-frequency reception signal (Sf_inter_Rx+Δf_inter_Rx) using the intermediate-frequency local signal (Sf_inter+Δf_inter).
G01S 7/35 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe - Détails de systèmes non impulsionnels
G01S 13/89 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la cartographie ou la représentation
G01S 7/03 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe - Détails de sous-ensembles HF spécialement adaptés à ceux-ci, p.ex. communs à l'émetteur et au récepteur
23.
METHOD FOR EVALUATING THE PERFORMANCE OF A PREDICTION ALGORITHM, AND ASSOCIATED DEVICES
The invention relates to a method for evaluating the performance of a prediction algorithm predicting the outputs for given inputs, the algorithm having been trained using a machine learning technique, the method including the steps of: obtaining data sets, each datum of a set corresponding to the outputs that the algorithm should give in the presence of the inputs of the set, receiving the probability that a set is observed, collecting the outputs predicted by the algorithm for each input of the data of the sets, determining the distribution of the prediction precision of the predicted output, aggregating the distributions determined by using an aggregation function using the probabilities received, and applying at least one risk metric to the aggregated distribution of prediction precision, for obtaining at least one indicator of the algorithm performance.
A winch includes a rotary drum, a cable which can be wound on the drum in multiple layers, and a brake for braking the rotation of the drum, the brake being calibrated to permit the rotation of the drum beyond a variable torque which decreases as the length of the cable wound on the drum increases.
Path extraction for a vehicle on a guideway, the vehicle having two or more sensors. Two or more sensor inputs are received from two or more sensors including at least one active 3D sensor input from at least one active 3D sensor and at least one passive 2D sensor input from at least one passive 2D sensor. At least one active 3D sensor path is extracted based on the at least one active 3D sensor input and at least one passive 2D sensor path based on the at least one passive 2D sensor input. At least one 3D sensor ground surface model is generated based on the at least one passive 2D sensor path. At least one passive 3D path is generated based on the at least one passive 2D sensor path and the at least one 3D sensor ground surface model. The at least one passive 3D path and the at least one active 3D sensor path are fused to produce a consolidated 3D path. In a path extraction pipeline, at least one supervision check is performed for providing integrity to the consolidated 3D path.
A digital method for tracing data from a plurality of data sources includes the steps of: a. obtaining initial data originating from a plurality of data sources, each initial datum comprising initial elements and initial connections, each initial element having a type and a value, b. determining a final datum on the basis of at least two initial data following the merging with one another of initial elements of the initial data according to a merging strategy, the merged initial elements making it possible to obtain a merged element having a type and a value, and c. determining a merging history for each merged element, the merging history comprising the type and the value of each initial element from which the merged element originates, the type and the value of the merged element, and data relating to the merging strategy.
G06F 16/901 - Indexation; Structures de données à cet effet; Structures de stockage
G06F 16/907 - Recherche caractérisée par l’utilisation de métadonnées, p.ex. de métadonnées ne provenant pas du contenu ou de métadonnées générées manuellement
27.
METHOD FOR DETERMINING VALLEY AREAS ACCESSIBLE BY AN AIRCRAFT
Disclosed is a method for determining valley areas accessible by an aircraft, the method being implemented by an electronic device, the method including the following steps: obtaining an initial image of an environment including areas of valleys; processing the initial image so as to eliminate the imaged elements on the initial image, the dimension of the elements being less than a predetermined dimension, to obtain a first processed image; and determining the curvature of each imaged element in the first processed image, the valley areas accessible by the aircraft being the imaged elements, in the first processed image, the curvature of which is strictly less than zero.
A multibeam satellite radiocommunications system includes at least one satellite having at least one passive multibeam antenna system, at least one satellite terminal, a resource allocator configured to form a regular network of satellite spots arranged according to a mesh in quadrilateral form over a given geographic zone, to associate spectral resources with the satellite spots, then to allocate spectral resources to the satellite terminals as a function of their position, wherein the resource allocator is configured to, in the event of failure of a satellite spot, extend the zone of coverage of the satellite spots adjacent to the failing satellite spot so as to cover the surface that it occupies, and allocate new spectral resources to the satellite terminals of the failing satellite spot as a function of their position. A resource allocator and the corresponding method are also provided.
Centre national de la recherche scientifique (France)
Inventeur(s)
Le Gall, Timothée
Ghiotto, Anthony
Morvan, Gwenaël
Varault, Stefan
Louis, Bruno
Pillet, Grégoire
Abrégé
The elementary antenna 1 includes: two cross-shaped slots 32, 33 defining four half-slots; for each half-slot, excitation striplines 41, 42, the first stripline 41 being connected to a first via 61 and the second stripline 42 being connected to a second via 62; an integrated circuit 70 delivering a plurality of ports; for each half-slot, tracks for feeding the strips, the first track 51 running from a first port 71 to the first via 61 and the second track 52 running from a second port 72 to the second via 62, the first and second ports being two successive ports of the integrated circuit, differentially connected to a transmitter/receiver channel by first and second power lines situated inside the integrated circuit, the lines and tracks running so that there is no crossing of the respective routes thereof.
H01Q 1/48 - ANTENNES, c. à d. ANTENNES RADIO - Détails de dispositifs associés aux antennes Écrans de terre; Contrepoids
H01Q 21/24 - Combinaisons d'unités d'antennes polarisées dans des directions différentes pour émettre ou recevoir des ondes polarisées circulairement ou elliptiquement ou des ondes polarisées linéairement dans n'importe quelle direction
30.
AUGMENTED REALITY THROUGH DIGITAL AIRCRAFT WINDOWS OF AIRCRAFT INFLIGHT ENTERTAINMENT SYSTEMS
An augmented reality (AR) system for an aircraft obtains an aircraft pose, determines a passenger pose relative to a window, and computes a field-of-view of the passenger. Operations select a set of passenger-relevant points of information (POIs) from a database that satisfy a relevance rule to the real-world objects viewable by the passenger through the window. For each of the passenger-relevant POIs in the set, operations determine an AR indicia to be displayed, and an AR indicia pose where the AR indicia is to be rendered on a display device. Operations generate a display command based on the AR indicia and the AR indicia pose for the passenger-relevant POIs in the set. Operations provide the display command to the display device to display renderings of the AR indicias with the AR indicia poses to augment the real-world objects viewed by the passenger through the window.
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
G06T 19/00 - Transformation de modèles ou d'images tridimensionnels [3D] pour infographie
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G06V 20/59 - Contexte ou environnement de l’image à l’intérieur d’un véhicule, p.ex. concernant l’occupation des sièges, l’état du conducteur ou les conditions de l’éclairage intérieur
G06V 40/10 - Corps d’êtres humains ou d’animaux, p.ex. occupants de véhicules automobiles ou piétons; Parties du corps, p.ex. mains
31.
NON-REDUNDANT PASSIVE MULTIBEAM SATELLITE RADIO-COMMUNICATIONS SYSTEM
The invention relates to a multibeam satellite radiocommunications system com prising: - at least one satellite having at least one passive multibeam antenna system, - at least one satellite terminal, - a resource allocator configured to form a regular network of satellite spots arranged according to a mesh in quadrilateral form over a given geographic zone, to associate spectral resources with the satellite spots, then to allocate spectral resources to the satellite terminals as a function of their position, in which the resource allocator is configured to, in the event of failure of a satellite spot (701), extend the zone of coverage of the satellite spots (702, 703, 704, 705) adjacent to the failing satellite spot so as to cover the surface that it occupies, and allocate new spectral resources to the satellite terminals of the failing satellite spot as a function of their position. The invention relates also to a resource allocator and the corresponding method.
A method for processing a signal from a coherent lidar comprising a periodically frequency-modulated coherent source (L), the method includes the following steps: A decomposing each modulation period indexed j into a plurality of intervals indexed i, and determining, for each interval Iij, an elementary power spectral density DSP(i,j) of the beat signal over the interval, B determining an average power spectral density over j DSP(i), C determining a lower frequency bound of the average power density DSP(i) and an upper frequency bound, D determining a distance dk(i) and a velocity of the fluid vk(i) from the lower and upper bounds.
G01S 17/34 - Systèmes déterminant les données relatives à la position d'une cible pour mesurer la distance uniquement utilisant la transmission d'ondes continues, soit modulées en amplitude, en fréquence ou en phase, soit non modulées utilisant la transmission d'ondes continues modulées en fréquence, tout en faisant un hétérodynage du signal reçu, ou d’un signal dérivé, avec un signal généré localement, associé au signal transmis simultanément
G01S 17/58 - Systèmes de détermination de la vitesse ou de la trajectoire; Systèmes de détermination du sens d'un mouvement
G01S 7/481 - Caractéristiques de structure, p.ex. agencements d'éléments optiques
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.
Some embodiments relate to a first connector, for coupling to a second connector, including a support structure, a set of spring-biased pogo pins arranged in a linear configuration and configured to carry at least one of electrical signals and power, a resilient structure extending across a face of the support structure, and a first pair of magnetic couplers attached to the resilient structure on opposite sides of the set of spring-biased pogo pins. The spring-biased pogo pins are each located in a corresponding passage in the support structure. The first pair of magnetic couplers are configured to mate with a corresponding second pair of magnetic couplers of the second connector and compress the resilient structure to bias the set of spring-biased pogo pins against a corresponding set of target contact pads of the second connector.
H01R 13/62 - Moyens pour faciliter l'engagement ou la séparation des pièces de couplage ou pour les maintenir engagées
H01R 13/24 - Contacts pour coopération par aboutage montés élastiquement
H01R 43/20 - Appareils ou procédés spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation de connecteurs de lignes ou de collecteurs de courant ou pour relier les conducteurs électriques pour assembler les pièces de contact avec le socle isolant, le boîtier ou le manchon ou pour les en désassembler
35.
SYSTEMS FOR PROVIDING A COMMON BATTERY PILOTING CHANNEL AND VEHICULAR AMPLIFIER ADAPTER RETENTION
A common battery for providing power to a first of a plurality of radios. The plurality of radios includes at least a first radio and a second radio. The common battery has a size of the smallest of at least two batteries. The common battery comprises a raised concentric wall edge for enabling the common battery to lock in place when used in place of a larger of the first battery and the second battery, such as within a Vehicular Adaptor Amplifier. The raised concentric wall edge has a height of a difference between a height of the first battery and a height of the second battery. In one variation, the common battery comprises a circular piloting interface that uses an outside radius of a respective bayonet connector on the first and second radios to align the common battery to the respective radio.
H01M 10/42 - Procédés ou dispositions pour assurer le fonctionnement ou l'entretien des éléments secondaires ou des demi-éléments secondaires
H01R 13/213 - Broches, lames ou alvéoles conformés ou ayant une pièce séparée en vue de retenir ensemble les parties en fonctionnement par connexion à baïonnette
36.
SYSTEMS FOR PROVIDING A COMMON BATTERY PILOTING CHANNEL AND VEHICULAR AMPLIFIER ADAPTER RETENTION
A common battery for providing power to a first of a plurality of radios. The plurality of radios includes at least a first radio and a second radio. The common battery has a size of the smallest of at least two batteries. The common battery comprises a raised concentric wall edge for enabling the common battery to lock in place when used in place of a larger of the first battery and the second battery, such as within a Vehicular Adaptor Amplifier. The raised concentric wall edge has a height of a difference between a height of the first battery and a height of the second battery. In one variation, the common battery comprises a circular piloting interface that uses an outside radius of a respective bayonet connector on the first and second radios to align the common battery to the respective radio.
H04B 1/3883 - Dispositions pour monter des batteries ou des chargeurs de batteries
H04B 1/3822 - TRANSMISSION - Détails des systèmes de transmission non caractérisés par le milieu utilisé pour la transmission Émetteurs-récepteurs, c. à d. dispositifs dans lesquels l'émetteur et le récepteur forment un ensemble structural et dans lesquels au moins une partie est utilisée pour des fonctions d'émission et de réception spécialement adaptés à l'utilisation dans des véhicules
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H01M 50/247 - Montures; Boîtiers secondaires ou cadres; Bâtis, modules ou blocs; Dispositifs de suspension; Amortisseurs; Dispositifs de transport ou de manutention; Supports spécialement adaptés aux dispositifs portatifs, p.ex. aux téléphones portables, aux ordinateurs, aux outils à main ou aux stimulateurs cardiaques
H01M 50/207 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules caractérisés par leur forme
H04M 1/02 - Caractéristiques de structure des appareils téléphoniques
37.
RADIOLOGY DEVICE WITH HELICALLY ARRANGED SOURCES AND DETECTOR
A radiology device includes a support capable of translational movement about an axis of translation relative to a frame of the device, the support being intended to support an object that is to be imaged, an ionizing-ray generator and a detector configured to detect the rays emitted by the generator, the generator and the detector facing one another. The generator comprises several sources each considered to emit from a focal point, the focal points of the various sources being distributed along a sources axis, the detector extending along a detector axis, the sources axis and the detector axis extending in the form of mutually intertwined helices about the axis of translation.
A device for receiving acoustic waves, includes an acoustic antenna able to function as a condenser microphone distributed along a line of the acoustic antenna comprising a conductor and a dielectric, the line being a transmission line or being configured to function as a transmission line when the dielectric makes direct physical contact with another conductor, an exciter configured to apply, in a receiving step, an input voltage to a first longitudinal end of the line so as to generate an input electromagnetic wave that moves toward a second longitudinal end of the line and so as to generate an output electromagnetic wave that moves in the opposite direction to the input electromagnetic wave, the input voltage simultaneously comprising a set of sinusoidal voltages comprising a fundamental sinusoidal voltage and a set of harmonics of the fundamental sinusoidal voltage, the frequency of the fundamental sinusoidal voltage being defined so that stationary waves are established in the line such that the output electromagnetic wave comprises directional acoustic-antenna channels.
A position of an aircraft is computed, associated with the radius of a sphere centered around the estimated position of the aircraft and within which the actual position of the aircraft is located with a probability equal to or greater than a predefined threshold. For this purpose, the computation is based on distances from radio transmitters each having a fixed position in a geographical reference frame. The positions of the radio transmitters are converted into a terrestrial reference system, before solving a system of equations linking, in the terrestrial reference system, the position of the aircraft and the positions of the radio transmitters. After solving the system of equations, the position of the aircraft is converted from the terrestrial reference system into the geographical reference frame.
G01S 19/07 - Systèmes de positionnement par satellite à radiophares émettant des messages horodatés, p.ex. GPS [Système de positionnement global], GLONASS [Système global de navigation par satellite] ou GALILEO Éléments coopérants; Interaction ou communication entre les différents éléments coopérants ou entre les éléments coopérants et les récepteurs fournissant des données pour corriger les données de positionnement mesurées, p.ex. DGPS [GPS différentiel] ou corrections ionosphériques
A method for detecting masking of one or more satellites by an obstacle for a GNSS receiver on board a movable carrier, including receiving, for each one of M satellites, a code pseudo-distance measurement and a variation of carrier pseudo-distances, computing of a definite position of the receiver and a computed position of each satellite, detecting a masking of at least one satellite on the basis of the following operations: computing, at a computation instant and for each satellite, of a computed pseudo-distance and a pseudo-distance reconstructed at a previous time, and detecting masking of at least one satellite by analyzing a magnitude, called residue, computed by applying a least squares algorithm.
A method of building a computer implemented data Classifier for Classifying data from a certain context is provided, whereby the Classifier is based on a model obtained by transfer learning combining Probabilistic Graphical Models (PGM) and arbitrary, context independent machine learned models enabled by special modelling patterns, where Variables representing outputs of machine learned models are added to the PGM.
G06N 5/01 - Techniques de recherche dynamique; Heuristiques; Arbres dynamiques; Séparation et évaluation
G06N 20/10 - Apprentissage automatique utilisant des méthodes à noyaux, p.ex. séparateurs à vaste marge [SVM]
B63G 13/00 - Autres aménagements offensifs ou défensifs sur les navires; Navires caractérisés à cet effet
G01S 13/00 - Systèmes utilisant la réflexion ou la reradiation d'ondes radio, p.ex. systèmes radar; Systèmes analogues utilisant la réflexion ou la reradiation d'ondes dont la nature ou la longueur d'onde sont sans importance ou non spécifiées
A method of building a computer implemented data classifier for classifying data from a certain context is provided, whereby the classifier is based on a model obtained by transfer learning combining Probabilistic Graphical Models (PGM) and arbitrary, context independent machine learned models enabled by special modelling patterns, where variables representing outputs of machine learned models are added to the PGM.
A method for generating at least one trajectory element (T) for controlling an aircraft (1) according to the trajectory element (T), the generation method being at least partially implemented by a generation system (2) on board the aircraft (1), and comprising the steps of:
receiving a first initial data stored in a first database (6), the first database (6) presenting a first predefined level of integrity, called the initial level of integrity;
receiving a second initial data stored in a second database (8), the second database (8) presenting said initial level of integrity, the first database (6) being dissimilar relative to the second database (8);
comparing at least one first trajectory data (D1) with at least one second trajectory data (D2);
obtaining the trajectory element (T).
The present invention relates to a magnetic push-button (10) comprises a fixed body and a body which is movable with respect to the fixed body along an axis of movement (X);
one of the bodies, called first body (21), comprising:
a magnetic element extending along the axis of movement (X) and defining a magnetic alternation along the axis of movement;
the other body, called second body (22), comprising:
a notching tooth made of ferromagnetic or magnetic material arranged opposite the magnetic element so as to create a push force by magnetic cooperation with the magnetic element, during a movement of the movable body (21) along the axis of movement (X);
a magnetic detector placed opposite the magnetic element and configured for generating measurements quantifying each movement of the movable body along the axis of movement (X).
An incremental magnetic encoder (10) defining an encoder axis (X) and comprising a fixed body and a body movable with respect to the fixed body along at least a first direction of encoding (C1).
An incremental magnetic encoder (10) defining an encoder axis (X) and comprising a fixed body and a body movable with respect to the fixed body along at least a first direction of encoding (C1).
One of the bodies, called first body (21), comprises a first ring extending along a first longitudinal direction coinciding with the encoder axis (X) and a first circumferential direction perpendicular to the first longitudinal direction, and defining a magnetic alternation along the first direction of encoding (C1). The other body, called second body (22), comprises at least one first notching tooth made of ferromagnetic or magnetic material arranged opposite the first ring, and a first pair of magnetic sensors arranged opposite the first ring and configured for quantifying each movement of the movable body along the first direction of encoding (C1).
G01D 5/14 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension
46.
Method of generating a peripheral image of an aircraft and associated electronic generation device and computer program product
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.
Procédé de génération d'au moins un élément de trajectoire (T) pour le contrôle d'un aéronef (1) selon l'élément de trajectoire (T), le procédé de génération étant au moins partiellement mis en oeuvre par un système de génération (2) embarqué dans l'aéronef (1), et comprenant des étapes de : - réception d'une première donnée initiale enregistrée dans une première base de données (6), la première base de données (6) présentant un premier niveau d'intégrité prédéfini, dit niveau d'intégrité initial ; - réception d'une seconde donnée initiale enregistrée dans une seconde base de données (8), la seconde base de données (8) présentant ledit niveau d'intégrité initial, la première base de données (6) étant dissimilaire par rapport à la seconde base de données (8) ; - comparaison d'au moins une première donnée de trajectoire (D1) avec au moins une seconde donnée de trajectoire (D2) ; - obtention de l'élément de trajectoire (T).
A viewing system intended to interact with a cranial mount, the viewing system includes a detachable displaying device, comprising: a combiner, placed in front of one eye of the user, and able to place information in superposition with an exterior view, the viewing system comprising a removable mounting interface configured to associate the displaying device with a plurality of cranial mounts among at least a helmet, a headband and a head-harness frame.
A method for calibrating the stiffness mismatch ΔK or quadrature Kxy of a vibrating angular sensor includes a resonator extending about two axes x and y defining a sensor frame xy, comprising a vibrating proof mass comprising two parts configured to vibrate in phase opposition with respect to each other in a direction x′ defining a wave frame x′y′, the direction x′ making an electrical angle to the axis x; and detection, excitation, quadrature compensation and stiffness adjustment transducers; the resonator having a stiffness matrix KC in the sensor frame and a stiffness matrix KO in the wave frame; the method comprising steps of: A determining the electrical angle; B recovering a quadrature or stiffness term of the stiffness matrix KO in the wave frame, the term being a sum of functions in cos(iθ) and sin(iθ); steps A and B being reiterated either for a plurality of electrical angles (θk), or for a duration during which the vibration wave continuously rotates through an electrical angle (θ(t)) varying as a function of time; C determining the amplitudes of the functions in cos(iθ) and sin(iθ); then D determining the stiffness mismatch ΔK or the quadrature Kxy, on the basis of the amplitudes.
G01C 25/00 - Fabrication, étalonnage, nettoyage ou réparation des instruments ou des dispositifs mentionnés dans les autres groupes de la présente sous-classe
G01C 19/574 - Dispositifs sensibles à la rotation utilisant des masses vibrantes, p.ex. capteurs vibratoires de vitesse angulaire basés sur les forces de Coriolis utilisant des masses planaires vibrantes entraînées dans une vibration de translation le long d’un axe - Details de structure ou topologie les dispositifs ayant deux masses de détection en mouvement en opposition de phase
A method of locating an aircraft in flight by means of a locating device including at least one sensor and a radar, the method including a first phase of determining a position of the aircraft, referred to as the first position, by means of the at least one sensor according to a signal supplied by the at least one sensor, a second phase of determining, at the same time as the first determination phase, a position of the aircraft, referred to as the second position, by means of the radar, and a phase of comparing data associated with the first position and data associated with the second position after which the first position is either validated or invalidated.
G01S 13/91 - Radar ou systèmes analogues, spécialement adaptés pour des applications spécifiques pour la commande du trafic
G01S 13/86 - Combinaisons de systèmes radar avec des systèmes autres que radar, p.ex. sonar, chercheur de direction
G01S 7/41 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe utilisant l'analyse du signal d'écho pour la caractérisation de la cible; Signature de cible; Surface équivalente de cible
A horn antenna including a ground plane delimiting an upper half-space, a horn forming one end of a waveguide, the horn crossing through the ground plane so that a mouth of the horn is arranged at a predetermined height above the ground plane in the upper half-space. The antenna is characterized in that it includes at least one resistive film arranged around the horn, parallel to an upper face of the ground plane, the resistive film having an electrical resistance suitable for limiting creeping waves.
The gateway, which connects a low-trust domain (12) and a high-trust domain (13) of an avionics computing infrastructure, provides a plurality of security functions, each function being performed by a data processing node. The gateway comprises, connected in series along a filtering chain of a data flow received from the low-trust domain: a firewall data processing node (4); a protocol break data processing node (5); a master data processing node (1) and an inverse protocol break data processing node (6), the gateway further including a security data processing node (2) connected to each of the data processing nodes of the filtering chain, the different data processing nodes being physically segregated.
An assembly for video display, includes a captive-air inflatable structure in a curved shape or a portion of a truncated sphere; a display medium; and a holding system between the inflatable structure and the display medium; the assembly wherein the holding system comprises hooks distributed over the surface of the concave part of the inflatable structure and complementary hooks distributed over the convex surface of the display medium; and in that all or some of the hooks are connected to complementary hooks positioned facing them, so that, when the inflatable structure is inflated, the hooks of the inflatable structure connected to complementary hooks of the display medium are stretched and make it possible to shape the display medium.
A computer-implemented method and system for providing adaptive training cursus to a trainee is disclosed. In the context of flight training for a given flight, the method allows providing training cursus recommendations by identifying every relevant phase (maneuvers and/or procedures) in a flight mission performed by a trainee; assessing the ease in flight of the trainee during each of these specific phases using an ease in flight algorithm model using psychophysiological parameters; and based on the conjunction of the ease in flight and predefined skills required to perform each phase, providing training cursus recommendations to target specifically the skills which are not yet mastered by the trainee.
G09B 9/08 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p.ex. bancs d'entraînement au pilotage sans visibilité
55.
Electronic system for monitoring the state of awareness of an operator in an aircraft, associated method and associated computer program
Centre national de la recherche scientifique (France)
Inventeur(s)
Berthelot, Bastien
Ibanez, Vincent
Becouarn, Loïc
Mazoyer, Patrick
Legrand, Pierrick
Grivel, Eric
Abrégé
An electronic system for monitoring the state of awareness of an operator in a control station of an aircraft. The monitoring system includes a module for receiving a datum from at least two sensors onboard the aircraft, at least one of the sensors being called a worn sensor being in physical contact with the operator and at least one of the sensors being called an off-set sensor being at a distance from the operator, a processing module configured for extracting from each datum at least one parameter representative of the state of awareness of the operator, a fusion module configured for receiving the representative parameters and implementing a machine learning method for determining, depending on the representative parameters, whether the operator is in a nominal or an altered state of awareness.
G06V 20/59 - Contexte ou environnement de l’image à l’intérieur d’un véhicule, p.ex. concernant l’occupation des sièges, l’état du conducteur ou les conditions de l’éclairage intérieur
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
56.
AUTOMATIC PARALLAX COMPENSATION FOR HELMET MOUNTED IMAGING SENSORS USED FOR AUGMENTED OR EXTENDED REALITY
A method, medium and system for compensating for parallax in transparent, semi-transparent, or opaque display components of a headband, headgear, head-worn device, or helmet-mounted device. A method for compensating for parallax in an image displayed on a display of a head-worn device (HWD) may include determining locations of one or more landmarks in a geographic space relative to a location of a user of the HWD based on first information indicative of the geographic space; generating a map of the one or more landmarks in the geographic space; receiving second information indicative of the geographic space; orienting the second information indicative of the geographic space relative to the map; shifting at least a portion of first or second information indicative of the geographic space to produce modified image data; and projecting the modified image data onto the screen of the head-worn device.
H04N 13/332 - Affichage pour le visionnement à l’aide de lunettes spéciales ou de visiocasques
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
H04N 13/239 - Générateurs de signaux d’images utilisant des caméras à images stéréoscopiques utilisant deux capteurs d’images 2D dont la position relative est égale ou en correspondance à l’intervalle oculaire
57.
DEVICE FOR CONTROLLING RF ELECTROMAGNETIC BEAMS ACCORDING TO THEIR FREQUENCY BAND, AND MANUFACTURING METHOD
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventeur(s)
Legay, Hervé
Stoumpos, Charalampos
Pierre, Thierry
Duran Venegas, Juan
Garcia Vigueras, Maria
Abrégé
A device for controlling radiofrequency beams of a given polarization, the device includes a set of at least one cell, comprising a support frame and at least one interconnection internal to the frame. The frame is inscribed within a prism, having a given axis Z′ and faces connected to one another by edges oriented along the axis Z′. The frame comprises corner elements, each having a rim coincident with an edge and being arranged such that the frame has, on each face, a slot (440-n) extending along the axis Z′. The interconnection comprises inductive rods, each comprising two ends of which a first end is connected to a rim, the second ends being connected to one another at a connection point positioned in the centre of the frame in a plane orthogonal to the axis Z′. Each cell is configured to carry out polarization-invariant transmission and/or reflection of beams.
A method, medium and system for compensating for parallax in transparent, semi-transparent, or opaque display components of a headband, headgear, head-worn device, or helmet-mounted device. A method for compensating for parallax in an image displayed on a display of a head-worn device (HWD) may include determining locations of one or more landmarks in a geographic space relative to a location of a user of the HWD based on first information indicative of the geographic space; generating a map of the one or more landmarks in the geographic space; receiving second information indicative of the geographic space; orienting the second information indicative of the geographic space relative to the map; shifting at least a portion of first or second information indicative of the geographic space to produce modified image data; and projecting the modified image data onto the screen of the head-worn device.
There is provided a method and a system for customized image denoising with interpretability. A deep neural network (NN) is trained to denoise an image on a training dataset including pairs of noisy and corresponding clean images acquired from an imaging apparatus, where during the training a structured covariance score (SCS) indicative of a performance of the deep NN in recovering content of corresponding clean images relative to the denoised image is determined based on sparse conditional correlations. A test noisy image is received and denoised by the deep NN. A user feedback score indicative of user satisfaction of the denoising is obtained. A quality parameter is obtained based on the SCS and a quality metric indicative of denoised image quality is obtained from a pretrained NN, and compared with the user feedback score. If the SCS is above the user feedback score, the deep NN is provided for denoising.
G06K 9/00 - Méthodes ou dispositions pour la lecture ou la reconnaissance de caractères imprimés ou écrits ou pour la reconnaissance de formes, p.ex. d'empreintes digitales
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventeur(s)
Legay, Herve
Stoumpos, Charalampos
Pierre, Thierry
Duran Venegas, Juan
Garcia Vigueras, Maria
Abrégé
What is proposed is a device (300) for controlling radiofrequency beams of a given polarization, the device comprising a set of at least one cell (400), comprising a support frame (420) and at least one interconnection (460) internal to the frame. The frame is inscribed within a prism, having a given axis Z' and Ar faces connected to one another by Ar edges oriented along the axis Z'. The frame comprises Ar corner elements, each having a rim coincident with an edge and being arranged such that the frame has, on each face, a slot (440-n) extending along the axis Z'. The interconnection comprises Ar inductive rods (462-n), each comprising two ends of which a first end is connected to a rim, the second ends being connected to one another at a connection point positioned in the centre of the frame in a plane orthogonal to the axis Z'. Each cell is configured to carry out polarization- invariant transmission and/or reflection of beams.
H01Q 15/10 - Dispositifs de réfraction ou diffraction, p.ex. lentille, prisme concernant un réseau de discontinuité d'impédance tridimensionnel, p.ex. trous dans une surface conductrice ou disques conducteurs formant diélectrique artificiel
61.
Integrated audio acquisition and playback module in electronic component form
An audio acquisition and reproduction module, embodied as an electronic component including a digital interface with a universal serial bus for audio signals, called a USB audio interface. The module includes a plurality of units which may be configured by means of a control link accessible by the USB audio interface, including a programmable computing unit including at least one processor configured to implement a plurality of audio signal processing operations, at least one analog/digital conversion unit for the acquisition and reproduction of analog audio signals, at least one reconfigurable analog interface, making it possible to make connections with at least one analog audio device, and at least one reconfigurable digital interface for making connections to at least one digital audio device.
A method for fitting a pre-existing standard helmet to the head of a user, the helmet includes an optronic device intended to be positioned in front of the eyes of the user, the method comprising: A) measuring the dimensions of the user's head, the dimensions of the head comprising a volume of the head and a position of the eyes, B) obtaining the dimensions of the helmet, the dimensions of the helmet including a volume of the helmet, C) defining a lining for the helmet so as to ensure the positioning of the optronic device in front of the user's eyes, the lining having a top face that is intended to be applied against an inner face of the helmet and a bottom face that is intended to be applied against the user's head, the lining having a flexible cellular structure, the manufacture of the lining being adapted to the dimensions of the head and to the dimensions of the helmet, D) manufacturing the lining as defined in step C), and E) placing the lining inside the helmet.
A device for centralized management of an aircraft flight management system is provided, of the type of human-machine interface called FMD (for Flight Management Display), and which includes a plurality of functional components associated with human-machine interfaces. In particular, the device comprises a component and its ‘waypoint list’ interface in order to display the list of waypoints of a flight plan, a component and its ‘flight-phase pages’ interface in order to meet a need in respect of construction of the flight plan, and of following and editing of the latter, a component and its ‘location and database management’ interface, and a component and its ‘system messages’ interface, the system messages being those of the flight manage system.
Systems and methods for improved human-machine dialog, include bidirectional translations notably through the translation of commands by the human into a form able to be manipulated by the machine, and conversely of results produced by the machine into a form intelligible to the human. Some developments describe notably the display of portions of intermediate reasoning followed by the machine (for example explanation of root causes).
G06F 40/35 - Représentation du discours ou du dialogue
G06N 3/086 - Méthodes d'apprentissage en utilisant les algorithmes évolutionnaires, p.ex. les algorithmes génétiques ou la programmation génétique
G06N 3/042 - Réseaux neuronaux fondés sur la connaissance; Représentations logiques de réseaux neuronaux
G06N 3/043 - Architecture, p.ex. topologie d'interconnexion fondée sur la logique floue, l’appartenance floue ou l’inférence floue, p.ex. systèmes d’inférence neuro-floue adaptatifs [ANFIS]
G05B 13/02 - Systèmes de commande adaptatifs, c. à d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
65.
SYSTEM AND METHOD FOR FAST AND RELIABLE DETECTION OF THE COMPLEXITY OF AIR SECTORS
In the field of air traffic control, a method is provided to determine a processing complexity of an ATC situation. For this purpose, the method includes grouping parameters of the paths by pairs of paths in a matrix, applying to this matrix a transformation aiming to concentrate the energy, then calculating the complexity index of the ATC situation as a function of the concentration level of the energy per component.
-- A method including acquisition of useful data during an experiment phase, the useful data being physiological data obtained by means of sensor(s) and each corresponding to an input data of the monitoring application, acquisition of declarative data of the individual, in real-time during the experimental phase and/or in differed time before and/or after the experimental phase, merging of useful data and declarative data in order to calculate a true level of fatigue, labeling the useful data with the calculated true level of fatigue, and storing the labeled useful data in the learning database.
G16H 50/20 - TIC spécialement adaptées au diagnostic médical, à la simulation médicale ou à l’extraction de données médicales; TIC spécialement adaptées à la détection, au suivi ou à la modélisation d’épidémies ou de pandémies pour le diagnostic assisté par ordinateur, p.ex. basé sur des systèmes experts médicaux
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
67.
Electronic device for monitoring a neurophysiological state of an operator in an aircraft control station, associated monitoring method and associated computer program
The invention relates to an electronic device for monitoring a neurophysiological state of an operator in a control station of an aircraft including a receiver module configured for receiving a datum from a sensor, a categorization module configured for associating, from the data received, a category with the operator, a processing module configured for extracting from each datum, at least one parameter representative of the neurophysiological state of the operator, and a detection module configured for applying a model derived from a machine learning method, for determining, according to the representative parameters, whether the operator is in a nominal neurophysiological state or in an altered neurophysiological state, the model being chosen from a list of predetermined models according to the category associated with the operator.
An acoustic transducer (30), comprising: a support structure (36); an active assembly comprising a base plate (32) supported by the support structure (36) and a piezoelectric body (34) supported by the base plate (32); and a passive vibrator (38) supported by the support structure (36) and coupled via the support structure (36) to the active assembly (32, 34) so that vibration of the active assembly (32, 34) drives the passive vibrator (38). The active assembly (32, 34) and the passive vibrator (38) have the same resonant frequency.
B06B 1/06 - Procédés ou appareils pour produire des vibrations mécaniques de fréquence infrasonore, sonore ou ultrasonore utilisant l'énergie électrique fonctionnant par effet piézo-électrique ou par électrostriction
G10K 11/00 - Procédés ou dispositifs pour transmettre, conduire ou diriger le son en général; Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général
H04R 1/28 - Supports de transducteurs ou enceintes conçus pour réponse de fréquence spécifique; Enceintes de transducteurs modifiées au moyen d'impédances mécaniques ou acoustiques, p.ex. résonateur, moyen d'amortissement
H04R 1/40 - Dispositions pour obtenir la fréquence désirée ou les caractéristiques directionnelles pour obtenir la caractéristique directionnelle désirée uniquement en combinant plusieurs transducteurs identiques
H04R 1/44 - Adaptation particulière pour usage sous l'eau, p.ex. pour hydrophone
A case for packaging electronic component(s), forming a housing intended to receive at least one electronic component, including a first support wall including an inner face suitable for receiving the electronic component(s), and an outer face, further includes a microfluidic cooling device made of a second material and inserted into the first support wall, the microfluidic cooling device including at least one channel for circulation of a heat-transfer fluid connected to a first inlet port for the heat-transfer fluid and to a second outlet port for the heat-transfer fluid, the cooling device including at least one platform for receiving the electronic component(s) in contact with the at least one channel for the circulation of a heat-transfer fluid.
H01L 23/473 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température impliquant le transfert de chaleur par des fluides en circulation par une circulation de liquides
70.
METHOD FOR SHARING DATA RELATING TO THE MANUFACTURING OF A PRODUCT
A method for sharing manufacturing data on a product includes a step of receiving data on the manufacturing state of the product, a step of generating new data on the manufacturing state of the product, and a step of transmitting the new state data to at least two RFID tags.
An imaging device employing backscattered x-ray photons, includes a plurality of x-ray sources, all configured to irradiate an analysis region wherein an object to be imaged may be placed, and a pixelated x-ray detector placed so as to detect x-ray photons potentially scattered by the object.
A method for processing a radiological image, in digital format includes at least one radiological anomaly detected using a convolutional neural network that has been trained to detect radiological anomalies on radiological examinations, the radiological image being characterized by the intensity of each of its pixels, and by at least one radiological anomaly influence map that assigns, for each pixel of the radiological image, a value representative of the proportion to which the pixel had an influence on the detection result of the radiological anomaly, which method is computer-implemented and comprises the steps of: normalizing the radiological anomaly influence maps to give normalized radiological anomaly influence maps; fusing the normalized radiological anomaly influence maps to give a single fused influence map; carrying out improvement processing on the image, using an intensity histogram, wherein the contribution of each pixel in the computing of the intensity histogram is weighted by the fused influence map.
THALES ALENIA SPACE ITALIA S.P.A. CON UNICO SOCIO (Italie)
Inventeur(s)
Ferroni, Stefano
Simone, Antonia
Abrégé
A connection unit comprising two female connectors configured to be connected to respective circuit branches of a fluidic line and a coupling element for coupling the connectors together and establish a fluidic connection between the circuit branches, wherein the connectors are provided with first, normally closed sealing elements to define a sealing termination of the circuit branches when the connectors are disconnected from each other; the coupling element includes a double-male connector separable from the female connectors and provided with a pair of shanks that can be coupled to the respective female connectors and a control element movable between a first position where the coupling element can be coupled to the connectors in a mechanical pre-coupling condition without fluidic connection between the female connectors and a second position where the shanks of the double-male connector engage the respective female connectors and establish a fluidic connection therebetween.
F16L 37/36 - Accouplements du type à action rapide avec moyens pour couper l'écoulement du fluide avec un obturateur dans chaque extrémité de tuyau avec deux clapets qui sont actionnés de façon que le courant à travers l'accouplement ne s'établisse qu'après l'accouplement sans désengagement possible
74.
Optical unit for a projective optical metrological system for determining quantities relative to the asset and/or position and communicating data
Thales Alenia Space Italia S.p.A. Con Unico Socio (Italie)
Scuola Superiore Di Studi Universitari E Perfezionamento Sant'Anna (Italie)
Inventeur(s)
Bresciani, Fulvio
Basso, Valter
Ciaramella, Ernesto
Cossu, Giulio
Rannello, Mario
Abrégé
Optical unit for a projective optical metrological system, which receives a light signal coming from a light constellation comprising a number of light sources; the optical unit includes: an optoelectronic image acquisition system and a first and a second optical circuit, which receive the light signal and are traversed by a first and a second optical beam, respectively. The first and the second optical circuits direct, respectively, at least a first part of the first optical beam and at least a first part of the second optical beam on the optoelectronic image acquisition system, so as to cause the simultaneous formation of two different images of the constellation in the optoelectronic image acquisition system. The optical unit further includes an electronic processing unit coupled to the optoelectronic image acquisition system, which determines a number of quantities indicative of the position and/or attitude of the light constellation with respect to the optical unit, based on the two images. The optical unit further includes an optical receiver and a derivation optical circuit configured to optically couple the optical receiver and at least one of the first and the second optical circuit, so that the optical receiver receives an optical information signal, which is a function of at least one of the first and the second optical beams. The optical receiver demodulates digital data from the optical information signal.
G01C 21/16 - Navigation; Instruments de navigation non prévus dans les groupes en utilisant des mesures de la vitesse ou de l'accélération exécutées à bord de l'objet navigant; Navigation à l'estime en intégrant l'accélération ou la vitesse, c. à d. navigation par inertie
G01C 21/02 - Navigation; Instruments de navigation non prévus dans les groupes par des moyens astronomiques
Thales Alenia Space Italia S.p.A Con Unico Socio (Italie)
Inventeur(s)
Ranieri, Paolo
Salvato, Antonio
Picchione, Elio
Cafaggi, Andrea
Abrégé
A capacitive feedthrough hermetically sealable to a hybrid module for space applications is provided that includes a multilayer ceramic structure including, on the top face, a metallized top central region designed to receive an input electrical signal to be filtered, a dielectric top region extending around the metallized top central region, and a metallized top peripheral region extending around the dielectric top region up to joining the metallized external closed side walls to act therewith as electrical ground; and, on the bottom face, a metallized bottom central region designed to provide an output filtered electrical signal, a dielectric bottom region extending around the metallized bottom central region, and a metallized bottom peripheral region extending around the dielectric bottom region up to joining the metallized external closed side walls to act therewith as electrical ground. The multilayer ceramic structure further includes ceramic layers, first metallized layers and one or more second metallized layers stacked on one another such that: each first metallized layer is interposed between two respective ceramic layers arranged immediately on and below said first metallized layer; each/the second metallized layer is interposed between two respective ceramic layers arranged immediately on and below said second metallized layer; the first and second metallized layers are vertically alternated such that each/the second metallized layer has a respective upper first metallized layer arranged above said second metallized layer, and a respective lower first metallized layer arranged below said second metallized layer; and two ceramic layers are respectively arranged immediately below the top face and immediately above the bottom face.
A high-voltage electrical connector for the space sector, includes a male portion and a female portion, which are intended to produce an electrical contact (CE) between the portions, the male portion comprising: a metallic male external shell; a male dielectric block encapsulated by the male shell and having a male structured region comprising what is called a male recess; the female portion comprising: a metallic female external shell, a female dielectric block encapsulated by the female shell and having a female structured region comprising a female recess; the male or female external shell having at least one opening, the male structured region having a shape that complements a shape of the female structured region, so that the male structured region is capable of being inserted into the female structured region in order to allow the electrical contact and so as to create a leakage duct between the female structured region and the male structured region allowing the air included between the female structured region and the male structured region to flow to the at least one opening.
H01R 13/53 - Socles ou boîtiers pour dures conditions de service; Socles ou boîtiers avec des moyens pour éviter l'effet couronne ou l'amorçage d'un arc
H01R 13/03 - Contacts caractérisés par le matériau, p.ex. matériaux de plaquage ou de revêtement
H01R 12/72 - Dispositifs de couplage pour circuits imprimés rigides ou structures similaires se couplant avec la bordure des circuits imprimés rigides ou des structures similaires
77.
BATTERY PACK WITH BATTERY CONTAINMENT SYSTEM COOLING GAS EXHAUSTED BY LITHIUM-ION BATTERY DURING THERMAL RUNAWAY CONDITION
Some embodiments of the present disclosure relate to a battery containment assembly for powering an electronic device. The battery containment assembly including at least one lithium-ion battery. The battery containment assembly includes a battery casing enclosing the at least one lithium-ion battery and having a cooling channel extending from a vent of the battery casing to the at least one lithium-ion battery, the cooling channel configured to vent any gas exhausted by the at least one lithium-ion battery to mix with air outside of the battery casing and to lower a temperature of the gas exhausted from the at least one lithium-ion battery during a thermal runaway condition of the at least one lithium-ion battery before the gas exits the vent.
H01M 10/6556 - Composants solides comprenant des canaux d'écoulement ou des tubes pour un échange de chaleur
H01M 10/613 - Refroidissement ou maintien du froid
H01M 10/653 - Moyens de commande de la température associés de façon structurelle avec les éléments caractérisés par des matériaux électriquement isolants ou thermiquement conducteurs
H01M 50/358 - Passages externes d’évacuation des gaz sur le couvercle ou sur le boîtier de batterie
A power stage includes a power transistor and a driver, the power transistor comprising a collector, a gate and an emitter and being configured to change over from a saturated state to an off state and vice versa in accordance with a control from the driver, the power stage comprising a resistor Rg positioned between the driver and the gate, the power stage comprising a circuit for compensating for delays that is positioned in parallel with the resistor Rg, comprising: a circuit for compensating for turn-on initialization delays, which is configured to divert the current from the resistor Rg when a saturation of the power transistor is initialized, a circuit for compensating for turn-off initialization delays, which is configured to divert the current from the resistor Rg when a switching-off of the power transistor is initialized, a circuit for compensating for delays that is configured to divert the current from the resistor Rg when the power transistor is close to the saturated state.
High-voltage electrical connector (1) for the space sector, comprising a male portion (M) and a female portion (F), which are intended to produce an electrical contact (CE) between the portions, said male portion comprising: - a metallic male external shell (CM); - a male dielectric block (DM) encapsulated by the male shell and having a male structured region (RSM) comprising what is called a male recess (RM); the female portion (F) comprising: - a metallic female external shell (CF) - a female dielectric block (DF) encapsulated by the female shell and having a female structured region (RSF) comprising a female recess (RF); the male or female external shell having at least one opening (O), the male structured region having a shape that complements a shape of the female structured region, so that the male structured region is capable of being inserted into the female structured region in order to allow the electrical contact and so as to create a leakage duct (AC) between the female structured region and the male structured region allowing the air included between the female structured region and the male structured region to flow to said at least one opening.
H01R 24/00 - Dispositifs de couplage en deux pièces, ou l'une des pièces qui coopèrent dans ces dispositifs, caractérisés par leur structure générale
H01R 13/533 - Socles ou boîtiers conçus pour l'emploi dans des conditions extrêmes, p.ex. haute température, rayonnements, vibrations, environnement corrosif, pression
H01R 13/629 - Moyens additionnels pour faciliter l'engagement ou la séparation des pièces de couplage, p.ex. moyens pour aligner ou guider, leviers, pression de gaz
The present invention relates to a device and a method for assisting aircraft guidance. The method for assisting aircraft guidance is operated by a computation platform for aircraft and comprises steps:
of acquisition of state variables characterizing an aircraft in flight, of environment variables characterizing the environment of the aircraft and of trajectory variables characterizing a reference trajectory of the aircraft;
of calculation of a predicted real trajectory for an upcoming change of direction of the aircraft, based on said state variables, on said environment variables and on said reference trajectory variables;
of determination of conformity to determine if the predicted real trajectory which is calculated conforms or does not conform to the reference trajectory; and
of configuration of a trajectory deviation alert, when the predicted real trajectory does not conform to the reference trajectory.
THALES ALENIA SPACE ITALIA S.P.A. CON UNICO SOCIO (Italie)
NEXT ONE FILM GROUP SRL (Italie)
Inventeur(s)
Tedone, Domenico
Basso, Valter
Bonavina, Alessandra
Abrégé
The invention concerns a method of providing a space extended reality service on earth, comprising: acquiring, by means of one or more acquisition systems/devices (1) installed on a space platform (2), real-time data related to a surrounding space environment and/or to one or more astronauts (3) in said space environment; generating, by means of a computer graphics processing device/system (4), based on the acquired real-time data and on synthetic data, a three-dimensional extended reality environment reproducing the space environment and one or more three-dimensional avatar(s) of the astronaut(s) (3) reproducing movements and/or actions and/or facial expressions and/or voice of said astronaut(s) (3), wherein the synthetic data digitally represent the space environment and/or the astronaut(s) (3); and providing one or more users (5) on earth with a space extended reality service based on the generated three-dimensional extended reality environment and avatar(s).
THALES ALENIA SPACE ITALIA S.P.A. CON UNICO SOCIO (Italie)
SIA "ALLATHERM" (Lettonie)
Inventeur(s)
Mishkinis, Donatas
Gottero, Marco
Abrégé
An evaporator assembly (2) including at. least one compensation chamber (10) and at least one capillary pump (11) comprising a primary wick (15), the evaporator assembly (2) including a secondary wick (16) extending through the at least one compensation chamber (10) and the at least one capillary pump (11) and contacting the primary wick (15) thereof; the least one compensation chamber (10) and the at least one capillary pump (11) are arranged parallel to one another along respective distinct axes (A, B).
F28D 15/02 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations dans lesquels l'agent se condense et s'évapore, p.ex. tubes caloporteurs
F28D 15/04 - Appareils échangeurs de chaleur dans lesquels l'agent intermédiaire de transfert de chaleur en tubes fermés passe dans ou à travers les parois des canalisations dans lesquels l'agent se condense et s'évapore, p.ex. tubes caloporteurs avec des tubes ayant une structure capillaire
83.
FLEXIBLE MEMBRANE PROVIDED WITH PHOTOVOLTAIC CELLS
A membrane capable of passing from a configuration wound about a first axis Z to a configuration deployed along a second axis X substantially perpendicular to the first axis Z, includes a. a main substrate comprising an upper surface covered at least partially with a first layer comprising a first thermoplastic polymer, b. at least one electrically conductive track, c. a photovoltaic unit comprising a secondary substrate and at least one photovoltaic cell fixed to an upper surface of the secondary substrate, the photovoltaic unit being designed to produce an electric current, and being electrically connected to the at least one electrically conductive track, the secondary substrate comprising a lower surface, opposite the upper surface of the secondary substrate and oriented towards the upper surface of the main substrate, the lower surface of the secondary substrate being covered at least partially with a second layer comprising a second thermoplastic polymer, the lower surface of the secondary substrate of the photovoltaic unit and the upper surface of the main substrate being at least partially heat welded.
A system including a module for acquiring source bases of terrain data corresponding to an area of a terrain, divided into a plurality of cells; each source base containing, for each cell, an elevation, a module for transposing each source base into a respective transposed base of terrain data corresponding to the area of terrain, divided according to a reference mesh into a plurality of transposed cells, each transposed base including, for each transposed cell, a transposed elevation, a module for evaluating a local consistency level, based on the comparison of the transposed elevation of the cell with the transposed elevation of the corresponding transposed cell of at least one other transposed base, and an assistance module configured to determine a navigation assistance datum for the aircraft, depending on the assessed local consistency level.
Disclosed is a method for detecting decoying of a traffic alert and collision avoidance system on-board an aircraft targeted by decoying. The method includes a phase of establishing a trusted network including the steps of dividing the space into a plurality of zones; and of selecting a verifier in each zone. The method further includes a phase of validation including the steps of generating an interrogation [sent] to each verifier; [a step of] reception of a response to each interrogation and verifying the response; and [a step of] analysis of all the responses so as to either validate or not validate the aircraft suspected of decoying, as false traffic.
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.
G01C 21/16 - Navigation; Instruments de navigation non prévus dans les groupes en utilisant des mesures de la vitesse ou de l'accélération exécutées à bord de l'objet navigant; Navigation à l'estime en intégrant l'accélération ou la vitesse, c. à d. navigation par inertie
G01C 23/00 - Instruments combinés indiquant plus d’une valeur de navigation, p.ex. pour l’aviation; Dispositifs de mesure combinés pour mesurer plusieurs variables du mouvement, p.ex. la distance, la vitesse ou l’accélération
G01C 21/08 - Navigation; Instruments de navigation non prévus dans les groupes par des moyens terrestres impliquant l'utilisation du champ magnétique terrestre
87.
METHOD FOR CALIBRATING A VIBRATING INERTIAL SENSOR
A method for calibrating an inertial angular sensor, includes the steps of: A for at least two electrical angles (θj) of the vibration wave: A1 applying, via each of the three trim controls CTi, a sinusoidal stiffness disturbance PSi having a disturbance frequency fi, and for each applied disturbance: A11 determining and storing an estimated excitation force Fei to be applied to the resonator in the presence of said disturbance PSi, on the basis of excitation controls determined by the servo controls, B determining, on the basis of the three estimated excitation forces Fei i=1, 2, 3 stored in step A11, three 2×2 matrices M′i, a matrix M′i being representative of the response of the gyrometer to the disturbance PSi, C determining and storing an estimated inverse excitation matrix (formula (A)) and an estimated inverse detection matrix (formula (B)) on the basis of the three matrices M′i determined in step B, an excitation matrix E and a detection matrix D being respectively representative of the effects of the excitation chain and of the effect of the detection chain of the sensor.
G01C 25/00 - Fabrication, étalonnage, nettoyage ou réparation des instruments ou des dispositifs mentionnés dans les autres groupes de la présente sous-classe
G01C 19/574 - Dispositifs sensibles à la rotation utilisant des masses vibrantes, p.ex. capteurs vibratoires de vitesse angulaire basés sur les forces de Coriolis utilisant des masses planaires vibrantes entraînées dans une vibration de translation le long d’un axe - Details de structure ou topologie les dispositifs ayant deux masses de détection en mouvement en opposition de phase
88.
THERMAL MITIGATION DEVICE FOR APPLICATION IN RADIO BATTERIES AND/OR ADAPTORS AND METHODS OF USE THEREOF
A portable radio device incorporating active thermal mitigation systems, and methods of use thereof. An example radio device incorporating an active thermal mitigation system may comprise a portable radio device selectively connectable or otherwise interoperable with a power adapter or battery device, wherein the power adapter or battery device includes an active thermal mitigation system. The system may include a micro-fan, blower, or other similar device configured to generate airflow, and may be configured to direct a flow of air or other fluid towards the radio device. The system may further include one or more fins or other features for directing and/or enhancing fluid flow, as well as sensors and control features to vary flow depending on temperature of the radio device or other variables.
A method for imaging a region of a moving blade of a wind turbine comprises using a wider field-of-view (WFoV) camera to capture a plurality of WFoV images of at least part of the moving blade in a field-of-view (FoV) of the WFoV camera, using the captured plurality of WFoV images of at least part of the moving blade to determine a trigger time when an edge of the moving blade is, or will be, in a triggering region, using the determined trigger time and a known spatial relationship between the triggering region and a FoV of a narrower field-of-view (NFoV) camera to calculate one or more NFoV image capture times when the edge of the moving blade, or a body of the moving blade, is, or will be, in the FoV of the NFoV camera, and using the NFoV camera to capture one or more NFoV images of the region of the moving blade at the calculated one or more NFoV image capture times. The one or more NFoV images of the region of the moving blade may be analysed to identify any damage or defects in the moving blade without any need to interrupt the motion of the blades of the wind turbine. The method may comprise sequentially scanning the FoV of the NFoV camera across a plurality of radial positions relative to an axis of rotation of the moving blades of the wind turbine and, for each radial position, imaging the corresponding regions of the moving blades of the wind turbine. The method may comprise performing the sequential scanning step and the imaging step autonomously according to a pre-programmed sequence to allow the imaging of both surfaces and both edges of each moving blade of the wind turbine.
A device for endorsing screwed assemblies, includes a screw gun intended to be handled by an operator, and computer equipment connected to the screw gun, the screw gun being equipped with measurement sensors sending information representative of the torque applied by the screw gun and an angle of rotation applied by the screw gun, the computer equipment storing, in a memory, reference data relating to a screwed assembly to be produced, the computer equipment being configured to compare information representative of the angle and the torque measured during the assembly with the reference data, and to provide a notification as to the conformity of the measurements of the angle and the torque in relation to the reference data.
B25B 23/147 - Agencement pour limiter le couple de blocage ou pour indiquer le couple des clés ou des tournevis spécialement adapté aux clés ou tournevis électriques
G05B 19/18 - Commande numérique (CN), c.à d. machines fonctionnant automatiquement, en particulier machines-outils, p.ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'u
91.
QUASI-OPTICAL BEAM FORMER WITH SUPERPOSED PARALLEL-PLATE WAVEGUIDE
The invention relates to a quasi-optical beam former (1) comprising a set of beam ports (6, 8), a set of network ports, a quasi-optical device and at least one parallel- plate waveguide (2, 3, 5) extending between the beam ports (6, 8) and the network ports, the beam ports (6, 8) and/or the network ports being superposed in at least two stages, each of the at least two stages being separated by a conductive plane (4) common to two adjacent stages, the quasi-optical beam former (1) comprising a resistive film (11) placed in the continuity of the conductive plane (4).
H01Q 15/00 - Dispositifs pour la réflexion, la réfraction, la diffraction ou la polarisation des ondes rayonnées par une antenne, p.ex. dispositifs quasi optiques
H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
A capacitive displacement sensor system with interdigitated combs, includes capacitive detection in a direction perpendicular to the surfaces of the combs facing one another, the combs being subjected to a sinusoidal movement in the direction, comprising: a device for converting the capacitance delivered by the sensor into a voltage; an analog/digital converter configured to digitize the voltage delivered by the conversion device, and supply a digitized signal; and a control unit comprising: a harmonic estimator configured to estimate the amplitudes of the harmonics of order less than or equal to a maximum order based on the digitized signal and a reference angle corresponding to the instantaneous angle of the input angular frequency; and a signal reconstruction module for reconstructing the signal from the amplitudes and the reference angle that are supplied by the harmonic estimator and from the digitized signal delivered by the analog/digital converter.
G01D 5/241 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensible; Moyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminé; Transducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier la capacité par mouvement relatif d'électrodes de condensateur
G01B 7/14 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la distance ou la marge entre des objets ou des ouvertures espacés
93.
QUASI-OPTICAL BEAM FORMER WITH SUPERPOSED PARALLEL-PLATE WAVEGUIDE
A quasi-optical beam former includes a set of beam ports, a set of network ports, a quasi-optical device and at least one parallel-plate waveguide extending between the beam ports and the network ports, the beam ports and/or the network ports being superposed in at least two stages, each of the at least two stages being separated by a conductive plane common to two adjacent stages, the quasi-optical beam former comprising a resistive film placed in the continuity of the conductive plane.
H01Q 19/10 - Combinaisons d'éléments actifs primaires d'antennes avec des dispositifs secondaires, p.ex. avec des dispositifs quasi optiques, pour donner à une antenne une caractéristique directionnelle désirée utilisant des surfaces réfléchissantes
94.
SYSTEM AND METHOD FOR BETTER DETERMINING PATH PARAMETERS OF AIRCRAFTS
A computer-implemented method is provided for training a supervised machine learning engine able to predict characteristics of aircraft trajectories from parameters of an aircraft, and environment parameters of the aircraft trajectory. A system able to train the supervised machine learning engine, a system for using the engine, and a computer-implemented method for using the engine are provided. The methods and systems provided are particularly useful for air traffic flow management applications.
A simplex Flight Control Computer (FCC), usable in conjunction with a neighboring FCC, includes an input providing module for receiving sensor, system and neighboring FCC data; a processing unit for executing a command partition and a monitor partition, the processing unit receives the sensor, system data and neighboring FCC data; the monitor partition monitors the neighboring FCC data and provides a monitoring indicative signal to the neighboring FCC, and the command partition generates command signals; a hardware monitoring module provides a validity signal indicating FCC health; an output cutoff module receiving the FCC validity signal and enable signals generated by each monitor partition; the output cutoff module providing an enable signal based on a predetermined enabling strategy; and an enable switch connected with the output cutoff module and the processing unit and providing a received signal from the command partition according to the enable signal.
A method for an object of interest in a degraded 2D digital image of the object is provided. The method includes the following steps: detecting, beforehand, the object of interest in a 2D digital image and assigning it a label; reconstructing a 3D volume of the object thus labeled from a plurality of available 2D digital images of the object of interest; storing, in a database, a record relating to the object thus reconstructed in 3D form and labeled; for each record thus stored, generating a new plurality of 2D digital images according to a plurality of viewing modes from the thus reconstructed 3D volume of each object; training a neural network on a learning set composed of an expanded set of 2D digital images thus generated and corresponding with the label of the object of interest to be recognized; from a degraded 2D digital image of the object of interest to be recognized; using the neural network thus trained to deliver as output the label of the object and a confidence index linked to the recognition of the object of interest.
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
G06V 10/774 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant l’intégration et la réduction de données, p.ex. analyse en composantes principales [PCA] ou analyse en composantes indépendantes [ ICA] ou cartes auto-organisatrices [SOM]; Séparation aveugle de source méthodes de Bootstrap, p.ex. "bagging” ou “boosting”
98.
SYSTEM AND METHOD FOR AUTOMATICALLY HARMONIZING THE POSITION AND/OR ORIENTATION BETWEEN AN APPARATUS ON BOARD A MOBILE CARRIER AND A REFERENCE FRAME OF THE MOBILE CARRIER
The invention relates to a system and a method for automatically harmonizing the position and/or orientation between an apparatus on board a mobile carrier and a reference frame of said mobile carrier, said mobile carrier being provided with an inertial unit able to provide measurements in the reference frame. The system comprises:
at least one accelerometer mechanically coupled to the onboard apparatus, and providing acceleration measurements in a reference frame referred to as the associated onboard apparatus,
a reception unit configured to receive measurements provided by said inertial unit and measurements provided by the accelerometer,
a computing unit configured to calculate values of parameters defining a geometric transformation for conversion of data from the reference frame of the carrier and the reference frame of the onboard apparatus, from the measurements, carried out for at least two different flight orientations, by said inertial unit and by said accelerometer.
Circuits are protected from timing attacks by adding a random delay to mask any relation between contents of processed information packages and the processing time required between in- and output signals of protected circuits. This random delay has to be performed preferably inside the protected volume and can be realized by one or more random delay buffers that are realized by means of e.g. random shift-registers. Further protection may be provided by situating the circuits in a single chip housing, such that the signals thereof interfere with each other and it is difficult to obtain information therefrom. A physical barrier may be provided in order to prevent or at least limit physical access to for example at least one TPM chip arranged inside of the barrier. The physical barrier comprises an impedance, i.e. in form of a capacitor with capacity C and or resistor R and or inductivity L, for example formed by two of the reflector layers of the barrier with an absorbing material in between. Any impedance (i.e. capacity C and/or resistance R and/or inductivity L) change can be detected and any impedance (i.e. capacity and/or resistance and/or inductivity L) change beyond a chosen threshold is indicative of an attempt to physically destruct or enter the barrier. Upon detecting an impedance (i.e. capacity C and/or resistance R and/or inductivity L) change beyond the threshold, any suitable action may be performed, such as deleting all information from the chip, destroying the chip or providing wrong information. The barrier may also act as a reflector for reflecting the desired signal of the at least one chip, such that the desired signal and the reflected signals interfere with each other and it is difficult to obtain information therefrom.
G06F 21/75 - Protection de composants spécifiques internes ou périphériques, où la protection d'un composant mène à la protection de tout le calculateur pour assurer la sécurité du calcul ou du traitement de l’information par inhibition de l’analyse de circuit ou du fonctionnement, p.ex. pour empêcher l'ingénierie inverse
G06F 21/87 - Boîtiers fiables ou inviolables par encapsulation, p.ex. de circuits intégrés
G06F 21/55 - Détection d’intrusion locale ou mise en œuvre de contre-mesures
G06F 21/74 - Protection de composants spécifiques internes ou périphériques, où la protection d'un composant mène à la protection de tout le calculateur pour assurer la sécurité du calcul ou du traitement de l’information opérant en mode dual ou compartimenté, c. à d. avec au moins un mode sécurisé
A protected circuit is provided comprising multiple essentially identical circuits, such as TPM (Trusted Platform Module) hosted in a common chip-housing, such that the signals thereof interfere with each other and it is difficult to obtain information therefrom. Additional protection may be achieved by adding a random delay to mask any relation between contents of processed information packages and the processing time required between in- and output signals of protected circuits. A physical barrier may be provided in order to prevent or at least limit physical access to for example at least one TPM chip arranged inside of the barrier. The physical barrier may comprises an impedance, i.e. in form of a capacitor with capacity C and or resistor R and or inductivity L, for example formed by two of the reflector layers with an absorbing material in between. Any impedance (i.e. capacity C and/or resistance R and/or inductivity L) change can be detected and any impedance (i.e. capacity and/or resistance and/or inductivity L) change beyond a chosen threshold is indicative of an attempt to physically destruct or enter the barrier. Upon detecting an impedance (i.e. capacity C and/or resistance R and/or inductivity L) change beyond the threshold, any suitable action may be performed, such as deleting all information from the chip, destroying the chip or providing wrong information. The barrier may also act as a reflector for reflecting the desired signal of the at least one chip, such that the desired signal and the reflected signals interfere with each other and it is difficult to obtain information therefrom.
G06F 21/85 - Protection des dispositifs de saisie, d’affichage de données ou d’interconnexion dispositifs d’interconnexion, p.ex. les dispositifs connectés à un bus ou les dispositifs en ligne
G06F 21/87 - Boîtiers fiables ou inviolables par encapsulation, p.ex. de circuits intégrés
G06F 21/75 - Protection de composants spécifiques internes ou périphériques, où la protection d'un composant mène à la protection de tout le calculateur pour assurer la sécurité du calcul ou du traitement de l’information par inhibition de l’analyse de circuit ou du fonctionnement, p.ex. pour empêcher l'ingénierie inverse