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公开(公告)号：US11762103B2
公开(公告)日：2023-09-19
申请号：US16993006
申请日：2020-08-13
Applicant: THALES
Inventor： Nicolas Martin , Denis Bouvet , Christian Mehlen
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.
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公开(公告)号：US20180100930A1
公开(公告)日：2018-04-12
申请号：US15715185
申请日：2017-09-26
Applicant: Thales
Inventor： Stéphane Corazza , Bruno Montagne , Denis Bouvet
IPC: G01S19/21
Abstract: A module making it possible to detect a disturbance signal during initial receiving by a receiver of navigation information, the receiver including a plurality of elementary antennas able to receive, in a plurality of arrival directions, electromagnetic signals including navigation information, a forming unit able to form a resultant signal from the electromagnetic signals and a processing unit able to process the resultant signal, the detection module being integrated into the forming unit and able to receive the electromagnetic signals coming from each of the elementary antennas, analyze the signals and detect a disturbance signal when the receiver is started cold in case of detection of a favored arrival direction of some of the electromagnetic signals.
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公开(公告)号：US10591611B2
公开(公告)日：2020-03-17
申请号：US15427595
申请日：2017-02-08
Applicant: THALES AVIONICS
Inventor： Nicolas Martin , Denis Bouvet
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.
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Patent Agency Ranking
公开(公告)号：US10520604B2
公开(公告)日：2019-12-31
申请号：US15715185
申请日：2017-09-26
Applicant: Thales
Inventor： Stéphane Corazza , Bruno Montagne , Denis Bouvet
Abstract: A module making it possible to detect a disturbance signal during initial receiving by a receiver of navigation information, the receiver including a plurality of elementary antennas able to receive, in a plurality of arrival directions, electromagnetic signals including navigation information, a forming unit able to form a resultant signal from the electromagnetic signals and a processing unit able to process the resultant signal, the detection module being integrated into the forming unit and able to receive the electromagnetic signals coming from each of the elementary antennas, analyze the signals and detect a disturbance signal when the receiver is started cold in case of detection of a favored arrival direction of some of the electromagnetic signals.
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公开(公告)号：US10670733B2
公开(公告)日：2020-06-02
申请号：US15465151
申请日：2017-03-21
Applicant: Thales
Inventor： Nicolas Martin , Denis Bouvet , Hervé Guichon
Abstract: The invention concerns a satellite geopositioning method on the basis of satellites each transmitting dual-frequency signals. The method comprises, for each satellite, a step of computation of four pseudo-distances on the basis of the two codes and the two carriers of the received dual-frequency geopositioning signals, a step of correction of the ionospheric delays over each computed pseudo-distance by applying an ionospheric error propagation model, a step of carrier code smoothing using a Kalman filter in order to provide a pseudo-distance measurement without measurement noise and to correct the residual ionospheric error. The position is estimated by using the corrected pseudo-distances computed for each satellite.
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公开(公告)号：US10649093B2
公开(公告)日：2020-05-12
申请号：US15946591
申请日：2018-04-05
Applicant: Thales
Inventor： Patrick Bartolone , Denis Bouvet
Abstract: A method for determining protection levels that comprises a preliminary phase carried out at least one time and a main phase carried out upon determining each new navigation solution. The preliminary phase comprises the steps of acquiring a first error value, providing a set of numbers of monitored faults, determining a plurality of computation coefficients, and storing the set of determined computation coefficients. The main phase includes the steps of determining a current number of monitored faults, and determining a protection level of the corresponding navigation solution by using an integrity relationship and the computation coefficients determined during the preliminary phase.
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7.发明申请公开(公告)号：US20190049590A1
公开(公告)日：2019-02-14
申请号：US15946591
申请日：2018-04-05
Applicant: Thales
Inventor： Patrick Bartolone , Denis Bouvet
Abstract: A method for determining protection levels that comprises a preliminary phase carried out at least one time and a main phase carried out upon determining each new navigation solution. The preliminary phase comprises the steps of acquiring a first error value, providing a set of numbers of monitored faults, determining a plurality of computation coefficients, and storing the set of determined computation coefficients. The main phase includes the steps of determining a current number of monitored faults, and determining a protection level of the corresponding navigation solution by using an integrity relationship and the computation coefficients determined during the preliminary phase.
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公开(公告)号：US20170276799A1
公开(公告)日：2017-09-28
申请号：US15465151
申请日：2017-03-21
Applicant: Thales
Inventor： Nicolas Martin , Denis Bouvet , Hervé Guichon
Abstract: The invention concerns a satellite geopositioning method on the basis of satellites each transmitting dual-frequency signals. The method comprises, for each satellite, a step of computation of four pseudo-distances on the basis of the two codes and the two carriers of the received dual-frequency geopositioning signals, a step of correction of the ionospheric delays over each computed pseudo-distance by applying an ionospheric error propagation model, a step of carrier code smoothing using a Kalman filter in order to provide a pseudo-distance measurement without measurement noise and to correct the residual ionospheric error. The position is estimated by using the corrected pseudo-distances computed for each satellite.
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