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

• US 9,244,174 B2
• Filed: 08/07/2013
• Issued: 01/26/2016
• Est. Priority Date: 08/07/2013
• Status: Active Grant

• Current Assignee: Topcon Positioning Systems Incorporated (Topcon Corporation)
• Original Assignee: Topcon Positioning Systems Incorporated (Topcon Corporation)
• Inventors: Averin, Sergey Vladislavovich, Nevzorov, Roman Anatolyevich, Plenkin, Andrey Valeryevich, Zubinsky, Vladimir Ivanovich
• Primary Examiner(s): Issing, Gregory C
• Application Number:
  US14/428,431
• Publication Number:
  US 20150226855A1
• Time in Patent Office: 902 Days
• US Class Current: 1/1
• CPC Class Codes: G01S 19/04 providing carrier phase data
• CPC Class Codes: G01S 19/073 involving a network of fixed stations
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G01S 19/426 by combining or switching between position solutions or signals derived from different modes of operation in a single system
• CPC Class Codes: G01S 19/428 using multipath or indirect path propagation signals in position determination
• CPC Class Codes: G01S 19/43 using carrier phase measurements, e.g. kinematic positioning; using long or short baseline interferometry

Abstract

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.

Claims

1. A method for processing global navigation satellite system (GNSS) measurements, the method comprising the steps of:

receiving a plurality of input GNSS measurements, wherein each input GNSS measurement in the plurality of input GNSS measurements has;

a corresponding navigation satellite in a plurality of navigation satellites; and

a corresponding carrier frequency in a plurality of carrier frequencies;

determining at least one group of input GNSS measurements, wherein;

the navigation satellite corresponding to each input GNSS measurement in each specific group of input GNSS measurements is the same; and

the carrier frequency corresponding to each input GNSS measurement in each specific group of input GNSS measurements is different;

for each specific group of input GNSS measurements;

selecting a first input GNSS measurement having a corresponding first carrier frequency;

selecting a second input GNSS measurement having a corresponding second carrier frequency;

calculating a geometry-free combination 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;

determining, based at least in part on the geometry-free combination parameter, whether a scintillation caused by an ionospheric irregularity has occurred; and

upon determining that a scintillation caused by an ionospheric irregularity has occurred;

generating a scintillation indicator corresponding to the specific group of input GNSS measurements.

2. The method of claim 1, further comprising the steps of:

determining whether at least one scintillation indicator has been generated; and

upon determining that at least one scintillation indicator has been generated;

generating an ionosphere-free combination parameter for each specific group of input GNSS measurements; and

calculating a target parameter based at least in part on the ionosphere-free combination parameters.

3. The method of claim 1, further comprising the steps of:

determining whether at least two scintillation indicators have been generated; and

upon determining that at least two scintillation indicators have been generated;

generating an ionosphere-free combination parameter for each specific group of input GNSS measurements having a corresponding scintillation indicator; and

calculating a target parameter based at least in part on the ionosphere-free combination parameters and based at least in part on the input GNSS measurements not used for generating an ionosphere-free combination parameter.

4. The method of claim 1, wherein, for each specific group of input GNSS measurements, the step of determining, based at least in part on the geometry-free combination parameter, whether a scintillation caused by an ionospheric irregularity has occurred, comprises the steps of:

calculating an estimate of a dispersion of the geometry-free combination parameter over a specified time interval;

comparing the estimate of the dispersion of the geometry-free combination parameter to a specified threshold value;

upon determining that the estimate of the dispersion of the geometry-free combination parameter is greater than the specified threshold value;

determining that a scintillation caused by an ionospheric irregularity has occurred; and

upon determining that the estimate of the dispersion of the geometry-free combination parameter is not greater than the specified threshold value;

determining that a scintillation caused by an ionospheric irregularity has not occurred.

5. The method of claim 1, wherein, in the step of determining at least one group of input GNSS measurements, the navigation satellite corresponding to each input GNSS measurement in each specific group of input GNSS measurements has a corresponding elevation angle greater than a specified threshold value.

6. The method of claim 1, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first code phase pseudo-range based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a navigation receiver;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second code phase pseudo-range based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the navigation receiver; and

the geometry-free combination parameter is calculated from the equation

GFC=(D₁−

D₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

D₁ represents the first code phase pseudo-range;

D₂ represents the second code phase pseudo-range;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

7. The method of claim 1, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first code phase pseudo-range difference based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a first navigation receiver in a rover and received by a second navigation receiver in a base station;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second code phase pseudo-range difference based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the first navigation receiver in the rover and received by the second navigation receiver in the base station; and

the geometry-free combination parameter is calculated from the equation

GFC=(Δ

D₁−

Δ

D₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

Δ

D₁ represents the first code phase pseudo-range difference;

Δ

D₂ represents the second code phase pseudo-range difference;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

8. The method of claim 1, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first carrier phase pseudo-range based at least in part on a first navigation signal having the first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a navigation receiver;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second carrier phase pseudo-range based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the navigation receiver; and

the geometry-free combination parameter is calculated from the equation

GFC=(φ

₁−

φ

₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

φ

₁ represents the first carrier phase pseudo-range;

φ

₂ represents the second carrier phase pseudo-range;

μ

=f₁²/f₂²

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

9. The method of claim 8, further comprising, for each specific group of input GNSS measurements, the steps of:

determining whether a cycle slip has occurred; and

upon determining that a cycle slip has occurred;

isolating the first input GNSS measurement and the second input GNSS measurement.

10. The method of claim 1, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first carrier phase pseudo-range difference based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a first navigation receiver in a rover and received by a second navigation receiver in a base station;

the second input GNSS measurement corresponding to the second carrier frequency comprises a second carrier phase pseudo-range difference based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the first navigation receiver in the rover and received by the second navigation receiver in the base station; and

the geometry-free combination parameter is calculated from the equation

GFC=(Δ

φ

₁−

Δ

φ

₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

Δ

φ

₁ represents the first carrier phase pseudo-range difference;

Δ

φ

₂ represents the second carrier phase pseudo-range difference;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

11. The method of claim 10, further comprising, for each specific group of input GNSS measurements, the steps of:

determining whether a cycle slip has occurred; and

upon determining that a cycle slip has occurred;

isolating the first input GNSS measurement and the second input GNSS measurement.

12. An apparatus for processing global navigation satellite system (GNSS) measurements, the apparatus comprising:

means for receiving a plurality of input GNSS measurements, wherein each input GNSS measurement in the plurality of input GNSS measurements has;

a corresponding navigation satellite in a plurality of navigation satellites; and

a corresponding carrier frequency in a plurality of carrier frequencies;

means for determining at least one group of input GNSS measurements, wherein;

the navigation satellite corresponding to each input GNSS measurement in each specific group of input GNSS measurements is the same; and

the carrier frequency corresponding to each input GNSS measurement in each specific group of input GNSS measurements is different;

means for, for each specific group of input GNSS measurements;

selecting a first input GNSS measurement having a corresponding first carrier frequency;

selecting a second input GNSS measurement having a corresponding second carrier frequency;

calculating a geometry-free combination 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;

determining, based at least in part on the geometry-free combination parameter, whether a scintillation caused by an ionospheric irregularity has occurred; and

upon determining that a scintillation caused by an ionospheric irregularity has occurred;

generating a scintillation indicator corresponding to the specific group of input GNSS measurements.

13. The apparatus of claim 12, further comprising:

means for determining whether at least one scintillation indicator has been generated; and

means for, upon determining that at least one scintillation indicator has been generated;

generating an ionosphere-free combination parameter for each specific group of input GNSS measurements; and

calculating a target parameter based at least in part on the ionosphere-free combination parameters.

14. The apparatus of claim 12, further comprising:

means for determining whether at least two scintillation indicators have been generated; and

means for, upon determining that at least two scintillation indicators have been generated;

generating an ionosphere-free combination parameter for each specific group of input GNSS measurements having a corresponding scintillation indicator; and

calculating a target parameter based at least in part on the ionosphere-free combination parameters and based at least in part on the input GNSS measurements not used for generating an ionosphere-free combination parameter.

15. The apparatus of claim 12, wherein, for each specific group of input GNSS measurements, the means for determining, based at least in part on the geometry-free combination parameter, whether a scintillation caused by an ionospheric irregularity has occurred, comprises:

means for calculating an estimate of a dispersion of the geometry-free combination parameter over a specified time interval;

means for comparing the estimate of the dispersion of the geometry-free combination parameter to a specified threshold value;

means for, upon determining that the estimate of the dispersion of the geometry-free combination parameter is greater than the specified threshold value;

determining that a scintillation caused by an ionospheric irregularity has occurred; and

means for, upon determining that the estimate of the dispersion of the geometry-free combination parameter is not greater than the specified threshold value;

determining that a scintillation caused by an ionospheric irregularity has not occurred.

16. The apparatus of claim 12, wherein, in the means for determining at least one group of input GNSS measurements, the navigation satellite corresponding to each input GNSS measurement in each specific group of input GNSS measurements has a corresponding elevation angle greater than a specified threshold value.

17. The apparatus of claim 12, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first code phase pseudo-range based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a navigation receiver;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second code phase pseudo-range based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the navigation receiver; and

the geometry-free combination parameter is calculated from the equation

GFC=(D₁−

D₂)(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

D₁ represents the first code phase pseudo-range;

D₂ represents the second code phase pseudo-range;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

18. The apparatus of claim 12, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first code phase pseudo-range difference based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a first navigation receiver in a rover and received by a second navigation receiver in a base station;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second code phase pseudo-range difference based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the first navigation receiver in the rover and received by the second navigation receiver in the base station; and

the geometry-free combination parameter is calculated from the equation

GFC=(Δ

D₁−

Δ

D₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

Δ

D₁ represents the first code phase pseudo-range difference;

Δ

D₂ represents the second code phase pseudo-range difference;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

19. The apparatus of claim 12, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first carrier phase pseudo-range based at least in part on a first navigation signal having the first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a navigation receiver;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second carrier phase pseudo-range based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the navigation receiver; and

the geometry-free combination parameter is calculated from the equation

GFC=(φ

₁−

φ

₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

φ

₁ represents the first carrier phase pseudo-range;

φ

₂ represents the second carrier phase pseudo-range;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

20. The apparatus of claim 19, further comprising, for each specific group of input GNSS measurements:

means for determining whether a cycle slip has occurred; and

means for, upon determining that a cycle slip has occurred;

isolating the first input GNSS measurement and the second input GNSS measurement.

21. The apparatus of claim 12, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first carrier phase pseudo-range difference based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a first navigation receiver in a rover and received by a second navigation receiver in a base station;

the second input GNSS measurement corresponding to the second carrier frequency comprises a second carrier phase pseudo-range difference based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the first navigation receiver in the rover and received by the second navigation receiver in the base station; and

the geometry-free combination parameter is calculated from the equation

GFC=(Δ

φ

₁−

Δ

φ

₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

Δ

φ

₁ represents the first carrier phase pseudo-range difference;

Δ

φ

₂ represents the second carrier phase pseudo-range difference;

μ

=f₁²/f₁²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

22. The apparatus of claim 21, further comprising, for each specific group of input GNSS measurements:

means for determining whether a cycle slip has occurred; and

means for, upon determining that a cycle slip has occurred;

isolating the first input GNSS measurement and the second input GNSS measurement.

23. A computer readable medium storing computer program instructions, which, when executed by a processor, cause the processor to perform a method for processing global navigation satellite system (GNSS) measurements, the method comprising the steps of:

receiving a plurality of input GNSS measurements, wherein each input GNSS measurement in the plurality of input GNSS measurements has;

a corresponding navigation satellite in a plurality of navigation satellites; and

a corresponding carrier frequency in a plurality of carrier frequencies;

determining at least one group of input GNSS measurements, wherein;

the navigation satellite corresponding to each input GNSS measurement in each specific group of input GNSS measurements is the same; and

the carrier frequency corresponding to each input GNSS measurement in each specific group of input GNSS measurements is different;

for each specific group of input GNSS measurements;

selecting a first input GNSS measurement having a corresponding first carrier frequency;

selecting a second input GNSS measurement having a corresponding second carrier frequency;

calculating a geometry-free combination 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;

determining, based at least in part on the geometry-free combination parameter, whether a scintillation caused by an ionospheric irregularity has occurred; and

upon determining that a scintillation caused by an ionospheric irregularity has occurred;

generating a scintillation indicator corresponding to the specific group of input GNSS measurements.

24. The computer readable medium of claim 23, wherein the method further comprises the steps of:

determining whether at least one scintillation indicator has been generated; and

upon determining that at least one scintillation indicator has been generated;

generating an ionosphere-free combination parameter for each specific group of input GNSS measurements; and

calculating a target parameter based at least in part on the ionosphere-free combination parameters.

25. The computer readable medium of claim 23, wherein the method further comprises the steps of:

determining whether at least two scintillation indicators have been generated; and

upon determining that at least two scintillation indicators have been generated;

generating an ionosphere-free combination parameter for each specific group of input GNSS measurements having a corresponding scintillation indicator; and

calculating a target parameter based at least in part on the ionosphere-free combination parameters and based at least in part on the input GNSS measurements not used for generating an ionosphere-free combination parameter.

26. The computer readable medium of claim 23, wherein, for each specific group of input GNSS measurements, the step of determining, based at least in part on the geometry-free combination parameter, whether a scintillation caused by an ionospheric irregularity has occurred, comprises the steps of:

calculating an estimate of a dispersion of the geometry-free combination parameter over a specified time interval;

comparing the estimate of the dispersion of the geometry-free combination parameter to a specified threshold value;

upon determining that the estimate of the dispersion of the geometry-free combination parameter is greater than the specified threshold value;

determining that a scintillation caused by an ionospheric irregularity has occurred; and

upon determining that the estimate of the dispersion of the geometry-free combination parameter is not greater than the specified threshold value;

determining that a scintillation caused by an ionospheric irregularity has not occurred.

27. The computer readable medium of claim 23, wherein, in the step of determining at least one group of input GNSS measurements, the navigation satellite corresponding to each input GNSS measurement in each specific group of input GNSS measurements has a corresponding elevation angle greater than a specified threshold value.

28. The computer readable medium of claim 23, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first code phase pseudo-range based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a navigation receiver;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second code phase pseudo-range based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the navigation receiver; and

the geometry-free combination parameter is calculated from the equation

GFC=(D₁−

D₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

D₁ represents the first code phase pseudo-range;

D₂ represents the second code phase pseudo-range;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

29. The computer readable medium of claim 23, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first code phase pseudo-range difference based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a first navigation receiver in a rover and received by a second navigation receiver in a base station;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second code phase pseudo-range difference based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the first navigation receiver in the rover and received by the second navigation receiver in the base station; and

the geometry-free combination parameter is calculated from the equation

GFC=(Δ

D₁−

Δ

D₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

Δ

D₁ represents the first code phase pseudo-range difference;

Δ

D₂ represents the second code phase pseudo-range difference;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

30. The computer readable medium of claim 23, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first carrier phase pseudo-range based at least in part on a first navigation signal having the first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a navigation receiver;

the second input GNSS measurement having the corresponding second carrier frequency comprises a second carrier phase pseudo-range based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the navigation receiver; and

the geometry-free combination parameter is calculated from the equation

GFC=(φ

₁−

φ

₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

φ

₁ represents the first carrier phase pseudo-range;

φ

₂ represents the second carrier phase pseudo-range;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

31. The computer readable medium of claim 30, wherein the method further comprises, for each specific group of input GNSS measurements, the steps of:

determining whether a cycle slip has occurred; and

upon determining that a cycle slip has occurred;

isolating the first input GNSS measurement and the second input GNSS measurement.

32. The computer readable medium of claim 23, wherein, for each specific group of input GNSS measurements:

the first input GNSS measurement having the corresponding first carrier frequency comprises a first carrier phase pseudo-range difference based at least in part on a first navigation signal having the corresponding first carrier frequency, wherein the first navigation signal is transmitted from the corresponding navigation satellite and received by a first navigation receiver in a rover and received by a second navigation receiver in a base station;

the second input GNSS measurement corresponding to the second carrier frequency comprises a second carrier phase pseudo-range difference based at least in part on a second navigation signal having the corresponding second carrier frequency, wherein the second navigation signal is transmitted from the corresponding navigation satellite and received by the first navigation receiver in the rover and received by the second navigation receiver in the base station; and

the geometry-free combination parameter is calculated from the equation

GFC=(Δ

φ

₁−

Δ

φ

₂)/(1−

μ

),

wherein;

GFC represents the geometry-free combination parameter;

Δ

φ

₁ represents the first carrier phase pseudo-range difference;

Δ

φ

₂ represents the second carrier phase pseudo-range difference;

μ

=f₁²/f₂²;

f₁ represents the corresponding first carrier frequency; and

f₂ represents the corresponding second carrier frequency.

33. The computer readable medium of claim 32, wherein the method further comprises, for each specific group of input GNSS measurements, the steps of:

determining whether a cycle slip has occurred; and

upon determining that a cycle slip has occurred;

isolating the first input GNSS measurement and the second input GNSS measurement.