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 1/42 - Arrangements or adaptations of power supply systems
B64G 1/10 - Artificial satellites; Systems of such satellites; Interplanetary vehicles
B64G 1/40 - Arrangements or adaptations of propulsion systems
B64G 1/62 - Systems for re-entry into the earth's atmosphere; Retarding or landing devices
B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
2.
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.
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)
Inventor
Attane, Jean-Philippe
Vila, Laurent
Bibes, Manuel
Abstract
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 - Digital stores characterised by the use of particular electric or magnetic storage elements; Storage elements therefor using magnetic elements using elements in which the storage effect is based on magnetic spin effect
G11C 19/08 - Digital stores in which the information is moved stepwise, e.g. shift registers using magnetic elements using thin films in plane structure
H10B 61/00 - Magnetic memory devices, e.g. magnetoresistive RAM [MRAM] devices
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 - Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing data for correcting measured positioning data, e.g. DGPS [differential GPS] or ionosphere corrections
8.
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)
Inventor
Delga, Alexandre
Espiau De Lamaestre, Roch
Abstract
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 for performing navigational calculations
11.
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.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Rondepierre, Alexandre
Rouchausse, Yann
Berthe, Laurent
Abstract
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 - Working by laser beam, e.g. welding, cutting or boring in a special environment or atmosphere, e.g. in an enclosure in a liquid, e.g. underwater
B23K 26/356 - Working by laser beam, e.g. welding, cutting or boring for surface treatment by shock processing
B23K 26/0622 - Shaping the laser beam, e.g. by masks or multi-focusing by direct control of the laser beam by shaping pulses
B23K 26/064 - Shaping the laser beam, e.g. by masks or multi-focusing by means of optical elements, e.g. lenses, mirrors or prisms
14.
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 - Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices with means for image conversion or intensification
G02B 7/12 - Adjusting pupillary distance of binocular pairs
G02B 27/14 - Beam splitting or combining systems operating by reflection only
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.
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 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group - Details of non-pulse systems
G01S 13/89 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging
G01S 7/03 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group - Details of HF subsystems specially adapted therefor, e.g. common to transmitter and receiver
22.
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.
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.
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)
Inventor
Le Gall, Timothée
Ghiotto, Anthony
Morvan, Gwenaël
Varault, Stefan
Louis, Bruno
Pillet, Grégoire
Abstract
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 21/24 - Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction
28.
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 - Systems determining position data of a target for measuring distance only using transmission of continuous waves, whether amplitude-, frequency-, or phase-modulated, or unmodulated using transmission of continuous, frequency-modulated waves while heterodyning the received signal, or a signal derived therefrom, with a locally-generated signal related to the contemporaneously transmitted signal
G01S 17/58 - Velocity or trajectory determination systems; Sense-of-movement determination systems
G01S 7/481 - Constructional features, e.g. arrangements of optical elements
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.
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 - Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing data for correcting measured positioning data, e.g. DGPS [differential GPS] or ionosphere corrections
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 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 - Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage
38.
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.
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 or analogous systems, specially adapted for specific applications for traffic control
G01S 13/86 - Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
G01S 7/41 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group using analysis of echo signal for target characterisation; Target signature; Target cross-section
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 - Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
47.
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)
Inventor
Berthelot, Bastien
Ibanez, Vincent
Becouarn, Loïc
Mazoyer, Patrick
Legrand, Pierrick
Grivel, Eric
Abstract
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.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Legay, Hervé
Stoumpos, Charalampos
Pierre, Thierry
Duran Venegas, Juan
Garcia Vigueras, Maria
Abstract
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.
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.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Legay, Herve
Stoumpos, Charalampos
Pierre, Thierry
Duran Venegas, Juan
Garcia Vigueras, Maria
Abstract
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 - Refracting or diffracting devices, e.g. lens, prism comprising three-dimensional array of impedance discontinuities, e.g. holes in conductive surfaces or conductive discs forming artificial dielectric
51.
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).
G06N 3/043 - Architecture, e.g. interconnection topology based on fuzzy logic, fuzzy membership or fuzzy inference, e.g. adaptive neuro-fuzzy inference systems [ANFIS]
G05B 13/02 - Adaptive control systems, i.e. systems automatically adjusting themselves to have a performance which is optimum according to some preassigned criterion electric
55.
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 - ICT specially adapted for medical diagnosis, medical simulation or medical data mining; ICT specially adapted for detecting, monitoring or modelling epidemics or pandemics for computer-aided diagnosis, e.g. based on medical expert systems
B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
57.
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.
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 - Arrangements for cooling, heating, ventilating or temperature compensation involving the transfer of heat by flowing fluids by flowing liquids
59.
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.
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.
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.
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.
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; Navigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigated; Dead reckoning by integrating acceleration or speed, i.e. inertial navigation
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
G01C 21/08 - Navigation; Navigational instruments not provided for in groups by terrestrial means involving use of the magnetic field of the earth
70.
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.
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 - Arrangement of torque limiters or torque indicators in wrenches or screwdrivers specially adapted for electrically operated wrenches or screwdrivers
G05B 19/18 - Numerical control (NC), i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
72.
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).
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 - Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying capacitance by relative movement of capacitor electrodes
G01B 7/14 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring distance or clearance between spaced objects or spaced apertures
74.
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 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
75.
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 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 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
G06V 10/774 - Generating sets of training patterns; Bootstrap methods, e.g. bagging or boosting
78.
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.
Method for controlling an unmanned aircraft piloted by a fully autonomous control system including a first decision module and a simplex piloting control module including a high-performance controller, a high-safety controller and a second decision module, the high-performance and high-safety controllers determining piloting commands for the robot-aircraft, according to which: —as long as a set of conditions is verified, implementation by the first decision module of a nominal piloting mode with delivery to the output of the automatic control system of the piloting commands delivered to the output of the simplex piloting control module; —otherwise, switching to an emergency piloting mode, an emergency piloting command is delivered to the output of the automatic control system for execution by the robot-aircraft, the first decision module preventing the delivery to the output of the automatic control system of the piloting commands delivered to the output of the simplex module.
Centre national de la recherche scientifique (France)
UNIVERSITE PARIS-SACLAY (France)
Inventor
Labreuche, Christophe
Bresson, Roman
Sebag, Martine
Cohen, Johanne
Abstract
The present invention relates to a method for generating a multiple-criteria decision support system comprising:
providing a problem and training data solving the problem for specific cases, the problem being a problem of evaluating the quality of a system chosen from:
choosing the best alternative from among alternatives,
distributing alternatives among classes,
the storage of alternatives in order of preference, and
providing a score of an alternative,
re-transcribing the problem according to a neural network and constraints to be observed,
training the re-transcribed neural network using the training data,
the determination of the function performed by the trained neural network, and
physically implementing the determined function in order to obtain the support system.
3-D OBJECT COMPRISING A SANDWICH OF ONE OR MORE COMPOSITE LAYERS, OF ONE OR MORE LAYERS OF METAL PATTERNS AND OPTIONALLY OF ONE OR MORE LAYERS OF POSSIBLY DENSE POLYMERS FOR ELECTROMAGNETIC APPLICATIONS IN ANTENNAS AND/OR RADOMES
A process for manufacturing a composite material of 3-D shape, includes a stack of layers of resin and fibre, incorporating at least one metal layer, the process comprising the following steps, a standard unit pattern having been determined for the metal layer: i/computing periodically organized patterns on the 3-D shape, which is non-developable; then projecting, onto a plane, the patterns, thus defining a planar organization of second patterns; ii/partially polymerizing, flat, first layers, comprising a metal top layer, of the flat composite stack, so as to make it etchable, but to keep it still deformable; iii/electrochemically etching the organization of second patterns that was defined in step i into the metal top layer of the flat composite stack resulting from step iv/carrying out polymerization of the etched composite stack after the stack has been placed in a mould having the desired 3-D shape.
B29C 64/147 - Processes of additive manufacturing using only solid materials using sheet material, e.g. laminated object manufacturing [LOM] or laminating sheet material precut to local cross sections of the 3D object
B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
B29C 64/188 - Processes of additive manufacturing involving additional operations performed on the added layers, e.g. smoothing, grinding or thickness control
82.
PASSIVE DIRECTIONAL RF ANTENNA SCANNABLE IN ONE OR TWO DIMENSIONS
A directional antenna array, to a radio-frequency antenna that includes one or more directional arrays and that is directional in one or two dimensions, and to a method for pointing the radio-frequency antenna and the associated computer program product. The directional antenna array comprises: a rectangular waveguide extending along a longitudinal axis, and comprising: a fixed portion with two lateral faces and an upper face, and a bottom part; a plurality of radiating elements placed on the fixed portion of the waveguide. The bottom part of the rectangular waveguide is movable translationally in a direction of movement parallel to the lateral faces, the maximum distance between the bottom part and the upper face being smaller than the distance between the lateral faces.
H01Q 3/44 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the electric or magnetic characteristics of reflecting, refracting, or diffracting devices associated with the radiating element
The method for calibrating a micromachined inertial angle sensor (2) comprising a support, at least one vibrating mass movable relative to the support, at least one transducer for exciting vibrating movement of the vibrating mass, at least one transducer for detecting a vibration of the vibrating mass, and at least one electrostatic transducer being capable of applying an adjustable electrostatic stiffness to the vibrating mass, the calibration method comprising the steps of the angle sensor receiving a predetermined vibrational excitation emitted by an excitation device (18) separate from the excitation transducer; the detection transducer measuring the vibration of the vibrating mass to obtain a measurement signal (Sm) from said measurement by the detection transducer; and transforming; determining, adjusting, and applying the electrostatic stiffness.
A component which is configured to switch an electrical signal, the component includes an insulating substrate bearing a semiconductor chip which ensures switching of the signal; a sole plate on which the substrate is secured, the sole plate being configured to discharge heat emitted during switching of the component; a conductive plane positioned between the sole plate and the insulating substrate, the conductive plane being insulated electrically against the sole plate; a specific component with impedance of at least 1 Ohm and/or at least 1 µH, by means of which the conductive plane is connected to a reference voltage.
H02M 7/5387 - Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters in a bridge configuration
H01L 23/46 - Arrangements for cooling, heating, ventilating or temperature compensation involving the transfer of heat by flowing fluids
H01L 23/00 - SEMICONDUCTOR DEVICES NOT COVERED BY CLASS - Details of semiconductor or other solid state devices
H02M 7/00 - Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
85.
METHOD AND SYSTEM FOR ASSISTING WITH THE APPROACH OF AN AIRCRAFT WITH A VIEW TO LANDING
An approach assistance method includes: an initial calculation step for calculating a reference path and the application of a stabilization test for determining whether the reference path makes the landing possible; modification steps implemented in a sequence and applying predefined modification rules and applying the stabilization test after each modification; and a transmitting step including transmitting the reference path to the human pilot, to an autopilot and/or to a traffic management system as soon as the reference path passes the stabilization test.
An imaging method using a doppler radar wherein the pointing direction in transmission (dei) is modified from recurrence to recurrence; each detection block of duration T comprises a periodic repetition of a number C of pointing cycles, each of these cycles comprising a number P of recurrences, the set of these P recurrences covering the De pointing directions (dei) of the set; the order of the pointings is modified in a pseudo-random manner from pointing cycle to pointing cycle during a same detection block so as to create an irregular time interval between two pointings in a same direction; at least one beam is formed in reception on each recurrence in a direction included in the transmission-focused angular domain in the pointing direction corresponding to the recurrence.
G01S 13/89 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging
G01S 7/35 - RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES - Details of systems according to groups , , of systems according to group - Details of non-pulse systems
G01S 13/58 - Velocity or trajectory determination systems; Sense-of-movement determination systems
87.
SYSTEM FOR CERTIFYING A PLANNED TRAJECTORY OF AN AIRCRAFT AND ASSOCIATED CERTIFICATION METHOD
Disclosed is a system for certifying a planned trajectory of an aircraft, the certification system being remote from the aircraft and including: a receiving device configured to receive the planned trajectory; a processing device including a plurality of processing modules, each processing module being configured to certify a given trajectory according to at least one certification rule specific to the processing module; a selection device configured to select one or more processing modules, which are referred to as active modules, to be used to certify the planned trajectory; a sending device configured to send a signal including a piece of certification information relating to the certification of the planned trajectory by all of the active modules.
Disclosed is a method of detecting spoofing of a traffic alert and collision avoidance system, known as a TCAS, the TCAS having a Mode A, a Mode C and a Mode S for communicating with surrounding aircraft. The method includes: querying a suspected spoofing aircraft via Mode S of the TCAS and receiving a response to this query; deducing from the response at least some data, known as Mode S data, relating to the suspected spoofing aircraft; and validating Mode S data by querying the suspected spoofing aircraft via Mode A or Mode C of the TCAS.
Centre national de la recherche scientifique (France)
Inventor
Champion, Jefferson
Mallegol, Stéphane
Pele, Ismaël
Goron, Erwan
Benedicto, Jessica
Martin, Noham Guy, Philippe
Allanic, Rozenn
Quendo, Cédric
Abstract
The disclosed antenna includes: a radiating element disposed in a radiating plane transverse to an axis of the antenna; a reflecting plane, which is transverse to the axis, the radiating plane being located at a predetermined height above the reflecting plane; and a substrate, interposed between the radiating plane and the reflecting plane, and having a constant thickness. This antenna is characterized by a local relative electrical permittivity of the substrate that is a function of the radius, i.e. the distance to the axis, and a height, i.e. a distance to the reflecting plane, the local relative electrical permittivity being, at constant height, increasing as a function of the radius, and, at constant radius, increasing as a function of the height at least for a portion of the substrate in the vicinity of the reflecting plane.
H01Q 13/20 - Non-resonant leaky-waveguide or transmission-line antennas; Equivalent structures causing radiation along the transmission path of a guided wave
H01Q 1/08 - Means for collapsing antennas or parts thereof
A system includes input or output channels linked to nominal and redundant equipment items, and at least one redundancy matrix for routing the signals of a channel from one equipment item to a redundant or nominal equipment item, represented by a connection grid having rows corresponding to the channels of the system and columns corresponding to the equipment items of the system, and connection points comprising: the points of intersection of a nominal path situated on a nominal diagonal of the connection grid, and the points of intersection of a redundant path of the connection grid situated between each row corresponding to a channel Ci and a column corresponding to a redundant element Rƒ(i) of index ƒ(i), f being surjective, the redundancy matrix being implemented in the form of a circuit comprising switches arranged according to the connection grid.
An elementary microstrip antenna includes a stack of layers, stacked in a direction z, the stack comprising: a first conductive radiating element of disc shape having a first centre, an axis in the direction z and passing through the first centre being called the central axis; a coupling assembly configured to couple an exciting device and the first radiating element, the coupling assembly comprising: a first slot comprising a centre called the slot centre located on the central axis; a second slot comprising a centre coincident with the slot centre, and substantially perpendicular to the first slot, the first and second slots each comprising circularly arcuate ends on the same circle centred on the slot centre; the slots and the stacked layers being configured so that a transverse footprint of the elementary antenna is disc-shaped.
Disclosed is a method for identifying a landing zone and for displaying on a head-up display system onboard an aircraft, a symbol conforming to the landing zone, the aircraft being apt to fly over a terrain and to land on the landing zone of the terrain. The aircraft is a helicopter, a drone or an electric aircraft with vertical take-off and landing. The method includes at least the following steps:—a hovering phase of the aircraft over the landing zone and acquisition of the geographical position of the landing zone;—a flight of the aircraft towards the landing zone and display on the head-up display system, of a symbol conforming to the landing zone at the measured geographic position.
Computer-implemented devices and methods for analysing navigation databases are provided, particularly including the steps of: comparing two databases and determining a list of different procedures between the databases (referred to as deviations); describing one or more of these procedures by N distinct flight scenarios, corresponding to different combinations of variations in flight parameter values (combinations of variations in performance, meteorological and/or speed parameters); in an aeronautical computer e.g. FMS, for one flight scenario, determining one or more flyable trajectories associated with one (or more or each) ΔP procedure. Developments describe determining operational impacts, machine learning processes, analyses of deviation by trajectory, by procedure or by deviations between procedures. System and software aspects are described.
Disclosed is a method of guiding the pilot of an aircraft for the alignment maneuver, including: determining at a first instant an occurrence close to the alignment maneuver and triggering the display of a first symbol on the screen; updating the position of the first symbol on the horizon according to the updated value of the aircraft heading; when the alignment maneuver is to begin, moving a second symbol on the screen from the position of the first symbol, the direction of the displacement with respect to the horizon being determined depending on the direction of the crosswind with respect to the runway and the value of the displacement being determined depending on the difference between the current dynamic sideslip of the aircraft and a current dynamic sideslip setpoint value calculated for the aircraft.
B64D 43/02 - Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
B64D 45/08 - Landing aids; Safety measures to prevent collision with earth's surface optical
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
The invention provides a system (100) comprising input or output channels linked to nominal and redundant equipment items, and at least one redundancy matrix (10) for routing the signals of a channel from one equipment item to a redundant (20') or nominal (20) equipment item, represented by a connection grid having rows corresponding to the channels of the system and columns corresponding to the equipment items (20, 20') of the system, and connection points comprising: - the points of intersection of a nominal path situated on a nominal diagonal of the connection grid, and - the points of intersection of a redundant path of the connection grid situated between each row corresponding to a channel Ci and a column corresponding to a redundant element Rgo of index f (i) , f being surjective, the redundancy matrix being implemented in the form of a circuit comprising switches arranged according to the connection grid.
96.
SOLID-STATE HYPERFREQUENCY AMPLIFIER AND POWER COMBINER COMPRISING FOUR SUCH SOLID-STATE AMPLIFIERS
A solidstate amplifier includes at least one interconnection, between a microstrip and a linearized impedance matching waveguide ridge, the interconnection being provided with a clamping device.
H03F 3/60 - Amplifiers in which coupling networks have distributed constants, e.g. with waveguide resonators
H01P 5/18 - Conjugate devices, i.e. devices having at least one port decoupled from one other port consisting of two coupled guides, e.g. directional couplers
H01P 5/02 - Coupling devices of the waveguide type with invariable factor of coupling
H03F 1/56 - Modifications of input or output impedances, not otherwise provided for
A method is provided for compensating time differences for the time alignment of uplink service frames and downlink service frames, the uplink service frames and the downlink service frames being exchanged between a satellite and a mobile terminal. The mobile terminal belonging to a 5G cell comprising a cell centre, the pre-compensation is calculated on the basis of a main beam directed towards the centre (O) of the cell (5G).
A satellite (SAT) includes a platform, at least one solar panel for supplying the satellite (SAT) with electrical energy, the solar panel being fixed along one side of the platform, the satellite comprising an antenna system (Rx+Z, Rx-Z, Tx+Z, Tx-Z) comprising two remote control antennas (Rx+Z, Rx-Z) and two remote measurement antennas (Tx+Z, Tx-Z), wherein the two remote control antennas (Rx+Z, Rx-Z) are disposed back to back on either side of the platform, and spaced one from the other by a distance less than or equal to λ, where λ corresponds to the wavelength of the remote control or remote measurement signal, the two remote measurement antennas (Tx+Z, Tx-Z) are disposed back to back, on either side of the platform, and spaced one from the other by a distance less than or equal to λ, the antenna system is disposed at one of the two ends of the side of the platform (PF) on which the solar panel (PS) is fixed.
A rotor of a rotating electrical machine includes a plurality of poles each extending on a first axis that is radial with respect to the rotor and on a second axis parallel to the rotor with respect to the rotor, each pole comprising a pole body, a rotor winding for each pole, positioned against the body of the pole, the rotor winding taking the form of a strip extending over the length of the pole body on the radial first axis wound against the pole body, a plurality of closure shims, a closure shim of the plurality of closure shims being in contact with a rotor winding associated with a pole body, the closure shim being configured to exert a pressure on the rotor winding towards the pole body.
A 5G communication system between at least one mobile terminal and a core network, the communication system includes at least one satellite, an access network comprising a plurality of base stations and a gateway disposed between the satellite and one of the base stations, the satellite and the gateway being able to exchange service frames comprising uplink service frames and downlink service frames, the uplink service frames having to be temporally aligned with the downlink service frames around a time reference point.