System and method for satellite positioning

Patent metadata

Field	Value
Publication number	US-11480690-B2
Application number	US-202117343327-A
Country	US
Kind code	B2
Filing date	Jun 9, 2021
Priority date	Jun 9, 2020
Publication date	Oct 25, 2022
Grant date	Oct 25, 2022

Abstract

A method and system for determining a receiver position comprising receiving satellite observations from a set of satellites, determining differenced observations based on the satellite observations, determining an all-in-view position of the receiver based on the differenced observations, determining a set of fault modes each associated with a subset of the differenced observations, for a fault mode of the set of fault modes, determining a fault-tolerant position of the receiver using the subset of differenced observations associated with the fault mode, when the all-in-view position and the fault tolerant position of the receiver for each fault mode are within a solution separation threshold, calculating a protection level associated with the all-in-view position of the receiver.

First claim

We claim:

1. A method for determining a receiver position comprising:
receiving a set of satellite carrier phase observations from a set of satellites;
receiving a set of reference observations from a set of reference stations;
determining double-differenced observations based on the set of satellite carrier phase observations and the set of reference observations;
estimating an all-in-view position of the receiver by processing the double-differenced observations using a snapshot least-squares calculation;
determining a set of fault modes, where each fault mode is associated with between one and N potentially faulty satellites, where N is a number of satellites in view of the receiver, wherein each fault mode is associated with a subset of the double-differenced observations with the potentially faulty satellites excluded;
for each fault mode:
determining a fault-tolerant position of the receiver by processing the double-difference observations in the respective fault mode;
comparing the all-in-view position and the fault tolerant position of the receiver;

when the all-in-position and the fault tolerant position of the receiver for each fault mode are within a solution separation threshold that depends on the covariances of the all-in-view receiver position, calculating a protection level associated with the all-in-view position of the receiver; and
when the all-in-view position and the fault tolerant position of the receiver for a fault mode differ by more than the solution separation threshold, determining a second set of double-differenced satellite observations that excludes observations associated with the potentially faulty satellites of the fault mode.

2. The method of claim 1 , wherein the protection level is calculated based on the covariances of the all-in-view receiver position.

3. The method of claim 1 , further comprising determining an integrity risk for each fault mode, wherein the integrity risk is determined based on the covariances.

4. The method of claim 3 , wherein determining the integrity risk comprises bounding a solution separation vector with a maximum bound on the solution separation threshold.

5. The method of claim 1 , further comprising determining operation instructions for a vehicle based on the all-in-view receiver position, wherein the receiver is mounted to the vehicle.

6. A method for determining a receiver position comprising:
receiving satellite observations from a set of satellites;
receiving reference observations from a set of reference receivers;
determining differenced observations based on the satellite observations and the reference observations;
determining an all-in-view position of the receiver based on the differenced observations;
determining a set of fault modes, each associated with a subset of the differenced observations, wherein each subset of the differenced observations excludes differenced observations associated with a distinct set of potentially faulty satellites;
for a fault mode of the set of fault modes, determining a fault-tolerant position of the receiver using the subset of differenced observations associated with the fault mode; and
when the all-in-view position and the fault tolerant position of the receiver for each fault mode are within a solution separation threshold, calculating a protection level associated with the all-in-view position of the receiver.

7. The method of claim 6 , further comprising, when the all-in-view position and the fault tolerant position of the receiver differ by more than the solution separation threshold, determining a second set of differenced satellite observations that excludes observations associated with the potentially faulty satellites associated with the fault mode, wherein the receiver position is determined based on the second set of differenced satellite observations.

8. The method of claim 7 , further comprising: when the potentially faulty satellites comprises a reference satellite, determining the second set of differenced observations using a second reference satellite.

9. The method of claim 7 , wherein the second set of differenced satellite observations are determined by transforming the satellite observations using a transformation matrix formed from the intersection of a differencing matrix and an identity matrix that excludes satellite observations associated with potentially faulty satellites.

10. The method of claim 9 , wherein the transformation matrix transforms the satellite observations to a second differenced observations set that is distinct from the differenced observations.

11. The method of claim 6 , wherein the solution separation threshold depends on variances and covariances of the all-in-view receiver position.

12. The method of claim 6 , wherein the difference observations comprise double-differenced observations.

13. The method of claim 6 , wherein the all-in-view receiver position using a snapshot least-squares calculation.

14. The method of claim 6 , wherein each set of potentially faulty satellites comprises at most a maximum number of potentially faulty satellites based on a probability that the maximum number of potentially faulty satellites have contemporaneous faults.

15. The method of claim 6 , wherein the satellite observations consist of satellite carrier phase data.

16. The method of claim 6 , wherein the difference observations are determined based on only satellite observations associated with resolved integer ambiguities.

17. The method of claim 16 , wherein integer ambiguities are resolved by:
determining a set of float phase ambiguities associated with the difference observations;
determining a set of integer phase ambiguity hypotheses using an integer search algorithm; and
selecting an integer phase ambiguity of the set of integer phase ambiguity hypotheses based on results of a hypothesis test comparing integer phase ambiguities of the set of integer phase ambiguity hypotheses.

18. The method of claim 6 , wherein the satellite observations and the reference observations are received during a first epoch, the method further comprising:
during a second epoch, receiving a second set of satellite observations from a second set of satellites;
during the second epoch, receiving a second set of reference observations from a second set of reference receivers;
determining a second all-in-view position of the receiver based on the second set of satellite observations and the second set of reference observations;
determining a second set of fault modes and a second fault-tolerant position of the receiver associated with a fault mode of the second set of fault modes; and
when the second all-in-view position and the second fault tolerant position are within the solution separation threshold, calculating a second protection level associated with the all-in-view position of the receiver.

19. The method of claim 18 , wherein the second set of fault modes is independent of the set of fault modes.

20. The method of claim 6 , further comprising determining operation instructions for a vehicle based on the all-in-view receiver position, wherein the receiver is mounted to the vehicle.

Assignees

• Swift Navigation Inc

Inventors

• Grgich Paul
• Maza Lloyd
• Brocard Philippe

Classifications

• G01S19/44

  Carrier phase ambiguity resolution; Floating ambiguity; LAMBDA [Least-squares AMBiguity Decorrelation Adjustment] method · CPC title

• G01S19/20 Primary

  Integrity monitoring, fault detection or fault isolation of space segment · CPC title

• G01S19/41 Primary

  Differential correction, e.g. DGPS [differential GPS] · CPC title