Topcon Positioning Systems, Inc.

Andrey Valerievich Plenkin

Mark Isaakovich Zhodzishsky

Andrey Vladimirovich Veitsel

Victor Abramovich Veitsel

Sergey Vladislavovich Averin

Dmitry Pavlovich Nikitin

Roman Anatolyevich Nevzorov

Victor Andreevich Prasolov

Vladimir Victorovich Veitsel

Viktor Abramovich Veitsel

Daniel Milyutin

Mikhail Yurievich Vorobiev

Vladimir Viktorovich Veitsel

Konstantin Viktorovich Ebauer

Danila Svyatoslavovich Milyutin

Vladimir Ivanovich Zubinsky

An apparatus for detecting global navigation satellite system (GNSS) spoofing, including a GNSS receiver that includes a first radio-frequency front-end (RF1) connected to antenna 1; a second radio-frequency front-end (RF2) connected to antenna 2; a digital section connected to both RF1 and RF2 and controlled with a single frequency oscillator. The digital section generates a first set of GNSS raw measurements based on signals received from antenna 1; generates a second set of GNSS raw measurements based on signals received from antenna 2; computes single differences between simultaneous raw measurements, generated with the signals received from the antenna 1 and the antenna 2 for the same GNSS satellite; compares the single differences with a threshold; and issues a spoofing alert when more than one of the single differences is below a threshold.

Method and apparatus for detecting GNSS spoofing

A high performance attitude determination system, including a global navigation satellite system (GNSS) receiver, the receiver including a first radio-frequency front-end (RF1) connected to a main antenna; a second radio-frequency front-end (RF2) connected to an auxiliary antenna; and a digital section connected to both RF1 and RF2. The digital section (i) generates a first set of GNSS raw measurements based on signals received from RF1; (ii) generates a second set of GNSS raw measurements based on signals received from RF2; (iii) computes a spatial attitude of a baseline between main and auxiliary antennas, using the first and the second sets of GNSS raw measurements, and based on carrier phase integer ambiguity resolution; (iv) continues updating the spatial attitude using the first and the second sets of GNSS raw measurements without carrier phase integer ambiguity resolution, and using fractional carrier phases. Optionally, RF1 and RF2 use a common clock.

High performance positioning system based on GNSS receiver with multiple front ends

A global navigation system includes a first navigation receiver located in a rover and a second navigation receiver located in a base station. Single differences of measurements of satellite signals received at the two receivers are calculated and compared to single differences derived from an observation model. Anomalous measurements are detected and removed prior to performing computations for determining the output position of the rover and resolving integer ambiguities. Detection criteria are based on the residuals between the calculated and the derived single differences. For resolving integer ambiguities, computations based on Cholesky information Kalman filters and Householder transformations are advantageously applied. Changes in the state of the satellite constellation from one epoch to another are included in the computations.

Detection and correction of anomalous measurements and ambiguity resolution in a global navigation satellite system receiver

A first plurality of differences (first differences or second differences) of carrier phase measurements of global navigation satellite system (GNSS) signals corresponding to a first measurement epoch is received. A plurality of differences of carrier phase ambiguities of the first plurality of differences of carrier phase measurements is resolved. A first fixed position of the rover is computed. A first plurality of sub-corrections is computed based at least in part on the first fixed position of the rover, a position of the base, a position of each specific GNSS satellite, and the first plurality of differences of carrier phase measurements. The first plurality of sub-corrections is then used to reduce the processing time for ambiguity resolution of carrier phase measurements in subsequent measurement epochs. The sub-corrections can be smoothed, aged, or smoothed and aged.

Reducing time and increasing reliability of ambiguity resolution in GNSS

A navigation receiver operating in a differential navigation mode transmits primary estimates of coordinates with an accuracy estimate that can vary during operation. To improve the positioning quality when the accuracy estimate changes, smoothed estimates of coordinates are generated according to a two-branch algorithm. The current-epoch accuracy estimate is compared to a current-epoch value of threshold accuracy. Upon determining that the current-epoch accuracy estimate is greater than or equal to the current-epoch value of threshold accuracy, the current-epoch smoothed estimates of coordinates are set equal to the current-epoch extended estimates of coordinates calculated from the sum of the previous smoothed estimates of coordinates and coordinate increments calculated from carrier phases. Upon determining that the current-epoch accuracy estimate is less than the current-epoch value of threshold accuracy, the current-epoch smoothed estimates of coordinates are generated based on the sum of the current-epoch extended estimates of coordinates and a correction signal.

Positioning quality of global navigation satellite system receivers

A scintillation caused by ionospheric irregularities during Global Navigation Satellite System (GNSS) measurements is detected. A first input GNSS measurement corresponding to a navigation satellite and corresponding to a first carrier frequency and a second GNSS measurement corresponding to the navigation satellite and corresponding to a second carrier frequency, in which the second carrier frequency is different from the first carrier frequency, are received. A geometry-free combination (GFC) parameter based at least in part on the first input GNSS measurement, the second input GNSS measurement, the first carrier frequency, and the second carrier frequency is calculated. The occurrence of a scintillation caused by an ionospheric irregularity is determined based at least in part on the GFC parameter. In an embodiment of the invention, the dispersion of the GFC parameter over a specified time interval is determined. A scintillation is detected if the dispersion exceeds a specified threshold value.

Detection of scintillations in signals of global navigation satellite systems caused by ionospheric irregularities

Scintillations caused by ionospheric irregularities during Global Navigation Satellite System (GNSS) measurements are detected and mitigated. Detection is based at least in part on statistical properties of geometry-free combination parameters calculated from input GNSS measurements corresponding to the same navigation satellite and different carrier frequencies. Mitigation is based at least in part on ionosphere-free combination parameters calculated from input GNSS measurements corresponding to the same navigation satellite and different carrier frequencies. Depending on the number of satellites with detected scintillations, different algorithms are used to calculate values of target parameters from a set of ionosphere-free combination parameters or from a set of ionosphere-free combination parameters and the remaining input GNSS measurements. Different algorithms accommodate stand-alone mode code phase measurements, stand-alone mode carrier phase measurements, differential navigation mode code phase measurements, and differential navigation mode carrier phase measurements.

Mitigation of scintillations in signals of global navigation satellite systems caused by ionospheric irregularities

The present invention relates to processing information generated by GNSS receivers received signals such as GPS, GLONASS, etc. GNSS receivers can determine their position in space. The receivers are capable of determining both coordinates and velocity of their spatial movement. When a receiver is used in any machine control systems, velocity vector heading (in other words, velocity vector orientation) should be determined along with velocity vector's absolute value. Angle, determining velocity vector orientation, is calculated based on velocity vector projections which are computed in navigation receivers. The accuracy of velocity vector orientation calculated based on velocity vector projections strongly enough depends on velocity vector's absolute value. To enhance the accuracy, a method of smoothing primary estimates of velocity vector orientation angles using a modified Kalman filter has been proposed. The bandwidth of this filter is varied depending on current estimates of velocity vector's absolute value which were calculated based on the same velocity vector projections.

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Moscow, Russia

Andrey Valerievich Plenkin