Abstract: 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.

Abstract: 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.

Abstract: A localization method, implemented in a satellite system includes at least a first constellation associated with a probability of occurrence of multiple failures lower than a given integrity risk, where the method may advantageously comprise the following steps implemented by a radioelectric device: receive a plurality of navigation signals; select failure modes to be monitored other than the multiple failures of the first constellation; determine a navigation solution and a plurality of navigation sub-solutions; calculate, for each navigation sub-solution, one or more corresponding detection thresholds; calculate one or more protection levels.

Abstract: 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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

Abstract: The invention relates to a method for acquisition of a signal (2) emitted by a satellite, by a receiver in a satellite Positioning System using a multi-code correlation and a multi-frequency correlation, also comprising the step in which if the error induced at the output from a first frequency-augmented correlator (14) at each instant in an integration period is greater than the code space between code correlators (12), the summated results of the first frequency-augmented correlator (14) are transferred to the summated results of a second frequency-augmented correlator (14), the second frequency-augmented correlator (14) using the same frequency-shift as the first frequency-augmented correlator (14) and being associated with a second code correlator (12) that is shifted by the code space from the first code correlator (12) with which said first frequency-augmented correlator (14) is associated.

Abstract: The invention relates to a method for acquisition of a signal (2) emitted by a satellite, by a receiver in a satellite Positioning System using a multi-code correlation and a multi-frequency correlation, also comprising the step in which if the error induced at the output from a first frequency-augmented correlator (14) at each instant in an integration period is greater than the code space between code correlators (12), the summated results of the first frequency-augmented correlator (14) are transferred to the summated results of a second frequency-augmented correlator (14), the second frequency-augmented correlator (14) using the same frequency-shift as the first frequency-augmented correlator (14) and being associated with a second code correlator (12) that is shifted by the code space from the first code correlator (12) with which said first frequency-augmented correlator (14) is associated.