公开(公告)号：US20240322936A1

公开(公告)日：2024-09-26

申请号：US18579897

申请日：2022-07-21

Applicant: THALES

Inventor： Nicolas MARTIN ,  Christian MEHLEN ,  David DEPRAZ

IPC: H04K3/00

CPC classification number: H04K3/25

Abstract: An electronic portion of a CRPA antenna of an anti-jamming device for a GNSS receiver, including M elementary signal inputs, for each input, a bandpass filter bank which is configured to break down each elementary signal received by this input at a frequency Fe, into P sub-bands to obtain P sub-sampled signals at a frequency Fe/P, a calculational component which is configured to apply in parallel anti-jamming processing at the frequency Fe/P to the sub-sampled signals, to obtain a cleaned sub-sampled signal, and a summation component which is configured to receive all the cleaned sub-sampled signals and to form, from these sub-sampled signals a resulting corresponding cleaned signal at the frequency Fe.

公开(公告)号：US20220351629A1

公开(公告)日：2022-11-03

申请号：US17733861

申请日：2022-04-29

Applicant: THALES

Inventor： Béatrice PESQUET-POPESCU ,  Nicolas MARTIN ,  Olivier RÉA ,  Andrei PURICA

IPC: G08G5/00 ,  G08G5/04 ,  G06N3/08

Abstract: A computer-implemented method includes receiving a trajectory request from an unmanned aerial vehicle, the request comprising: an initial point; a final point; at least one manoeuvrability parameter of the unmanned aerial vehicle; computing a plurality of optimized 4D trajectories between the initial point and the final point, complying with the at least one manoeuvrability parameter, and avoiding obstacles in an airspace, each 4D trajectory being associated with a performance score; a flight simulator simulating the plurality of 4D trajectories in order of decreasing performance score, until a 4D trajectory is considered to be flyable by the flight simulator; sending the trajectory considered to be flyable by the flight simulator to the unmanned aerial vehicle.

公开(公告)号：US20230393289A1

公开(公告)日：2023-12-07

申请号：US18249251

申请日：2021-10-25

Applicant: THALES

Inventor： Nicolas MARTIN ,  Muhammed HALEP ,  Christian MEHLEN

IPC: G01S19/51

CPC classification number: G01S19/51

Abstract: 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.

公开(公告)号：US20230015165A1

公开(公告)日：2023-01-19

申请号：US17787327

申请日：2020-12-10

Applicant: THALES

Inventor： Nicolas MARTIN ,  Maxime TESSIER ,  Isabelle LEBLANC

IPC: G08G5/00 ,  G08G5/04

Abstract: A method for automatically proposing an air conflict resolution, the method includes a step of receiving air conflict and air situation data at a time when an air conflict is detected, the method comprising the steps of: determining a conflict category associated with the detected air conflict based on the conflict data; determining a degree of relevance in proposing a resolution to the air conflict according to the category and the air situation; determining one or more types of resolution to be applied to resolve the detected air conflict according to the degree of relevance; determining set of alternative trajectories corresponding to the one or more types of resolution; determining a set of candidate trajectories from among the set of alternative trajectories, a candidate trajectory being an alternative trajectory which does not generate an air conflict; selecting, from among the candidate trajectories, a candidate trajectory which fulfills a selection criterion relating to the operational relevance of the candidate trajectories and to the acceptability of the candidate trajectories by the flight plan management system; returning the candidate trajectory, the candidate trajectory being saved and re-evaluated as long as it does not generate an air conflict or has not been accepted by an air traffic controller.

公开(公告)号：US20240176359A1

公开(公告)日：2024-05-30

申请号：US18515168

申请日：2023-11-20

Applicant: THALES

Inventor： Guillaume HEREDIA ,  Arthur MOUSSIERE ,  Loïc CHACORNAC ,  Nicolas MARTIN ,  Paul DE COURCEL

IPC: G05D1/04

CPC classification number: G05D1/042 ,  B64U2101/00

Abstract: A method for controlling an unmanned aircraft includes determining a maximum flying altitude for a ground position of the aircraft, the method comprising: for each point from a plurality of ground points situated within a perimeter around the ground position of the aircraft, referred to as “surrounding points”, determining one or more intersections between firstly a circle, the centre of which is the point and the radius of which is the maximum authorized ground distance at this point, referred to as the “determination circle”, and secondly a vertical related to the ground position of the aircraft, the circle being contained in a vertical plane comprising the vertical related to the ground position of the aircraft; and for all of the intersections thus obtained, selecting the greatest altitude as the maximum flying altitude.

公开(公告)号：US20170227652A1

公开(公告)日：2017-08-10

申请号：US15427595

申请日：2017-02-08

Applicant: THALES AVIONICS

Inventor： Nicolas MARTIN ,  Denis BOUVET

IPC: G01S19/23

Abstract: A method for determining a wrong synchronization of a receiver with a satellite, associated receiver and computer program product, is implemented after the acquisition phase and includes the following steps: generating first and second test signals; for each correlation interval, determining a first prompt correlator corresponding to the correlation value between the received signal and the first test signal, and a second prompt correlator corresponding to the correlation value between the received signal and the second test signal; determining first and second energy values corresponding to the energy of the first and second correlators, respectively; determining a wrong synchronization indicator based on the difference between the first and second energy values; and detecting a wrong synchronization based on this indicator.

公开(公告)号：US20170139051A1

公开(公告)日：2017-05-18

申请号：US15348211

申请日：2016-11-10

Applicant: THALES

Inventor： Nicolas MARTIN ,  Yves CLAUZEL

IPC: G01S19/23

CPC classification number: G01S19/23 ,  G01S19/21 ,  G01S19/30

Abstract: This determination method for determining a wrong synchronization including the steps of determining an ad hoc correlator corresponding to the value of correlation between the received signal and the local signal, and determining N additional correlators corresponding to the values of correlation between the received signal and an offset signal, each offset signal including a spreading code that is offset in relation to the local spreading code, and determining a value for the amount of inconsistency between the frequency of the local carrier wave and the frequency of the local spreading code; if the value of inconsistency is higher than a predetermined threshold value of inconsistency, determining a wrong synchronization; otherwise, determining an indicator of wrong synchronization as a function of the correlators determined, comparing the indicator of wrong synchronization with at least one threshold value, determining a wrong synchronization based on the result of the comparison.

公开(公告)号：US20230366701A1

公开(公告)日：2023-11-16

申请号：US18029890

申请日：2021-10-08

Applicant: THALES

Inventor： Nicolas VERCIER ,  Nicolas MARTIN

IPC: G01C25/00 ,  G01C19/574

CPC classification number: G01C25/005 ,  G01C19/574

Abstract: 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.

公开(公告)号：US20210048536A1

公开(公告)日：2021-02-18

申请号：US16993006

申请日：2020-08-13

Applicant: THALES

Inventor： Nicolas MARTIN ,  Denis BOUVET ,  Christian MEHLEN

IPC: G01S19/23 ,  G01S19/30 ,  G01S19/39

Abstract: This detection method is carried out after a phase for acquiring a navigation signal during a convergence phase and comprises at least one of the following steps: —determining a plurality of pilot channel periodic correlations and a plurality of data channel periodic correlations, and determining a first value as a function of these periodic correlations; —determining a plurality of pilot channel partial correlations, and determining a second value as a function of these partial correlations; —determining a plurality of shifted pilot channel correlations, and determining a third value as a function of these shifted pilot channel correlations.
The convergence phase further comprises the step for determining a wrong synchronization when at least one of the first value, the second value, and the third value exceeds a predetermined threshold.

公开(公告)号：US20200292711A1

公开(公告)日：2020-09-17

申请号：US16814870

申请日：2020-03-10

Applicant: THALES

Inventor： Nicolas MARTIN ,  Daniel MILLWOOD ,  Stéphane ROLLET

IPC: G01S19/20 ,  G01S19/21

Abstract: A method and a function for checking the integrity of the processing of a radionavigation signal emitted by a satellite, the signal being received by a receiver comprising reception means and processing means, the processing means comprising a linear anti-interference filter, the integrity checking method comprising at least a first phase of detection of a risk of false lock-on comprising the following steps: a step of recovery of a nominal theoretical self-correlation function of the received signal not processed by the linear anti-interference filter; a step of determination of a mean theoretical self-correlation function of the signal received and processed by the linear anti-interference filter over a defined integration period; a step of determination of the number of local maxima of the modulus or of the modulus squared of the mean theoretical self-correlation function, a risk of false lock-on being detected if the number of local maxima is greater than or equal to two.