GNSS positioning using pressure sensors

• US 8,949,025 B2
• Filed: 06/04/2008
• Issued: 02/03/2015
• Est. Priority Date: 06/08/2007
• Status: Expired due to Fees

• Current Assignee: Qualcomm, Inc.
• Original Assignee: Qualcomm, Inc.
• Inventors: Garin, Lionel J.
• Primary Examiner(s): To, Tuan C.
• Assistant Examiner(s): Kan, Yuri
• Application Number:
  US12/599,258
• Publication Number:
  US 20100204916A1
• Time in Patent Office: 2,435 Days
• Field of Search: 342/357.28, 342/357.3, 342/357.48, 701/208, 701/4, 701/11, 701/45, 701/46, 701/457, 701/475, 701/532, 701/472, 702/150, 280/734, 280/735, 280/736, 280/738, 375/350
• US Class Current: 701/532
• CPC Class Codes: G01C 5/005 altimeters for aircraft G01C5/02, G01C5/06 take precedence
• CPC Class Codes: G01L 19/08 Means for indicating or recording, e.g. for remote indication
• CPC Class Codes: G01S 19/22 Multipath-related issues
• CPC Class Codes: G01S 19/45 by combining measurements of signals from the satellite radio beacon positioning system with a supplementary measurement

Abstract

Systems, methods and devices for improving the accuracy of GNSS data are provided. Specifically, embodiments of the invention can advantageously use sensor input to improve the accuracy of position fixes. The use of physical sensors in navigation systems is deemed particularly advantageous, especially where altitude data derived from the pressure sensor is calibrated with and/or blended with GNSS altitude data.

Claims

1. A navigation receiver comprising:

a pressure sensor configured to provide a pressure sensor signal;

a GNSS receiver configured to provide pseudoranges;

a microprocessor configured to compute;

(1) a GNSS altitude and a vertical pseudorange residue derived from the pseudoranges, (2) a barometric altitude derived from the pressure sensor signal, based on an atmospheric model, and (3) a double difference in altitude based on a difference between a GNSS altitude variation and a barometric altitude difference; and

a Kalman filter configured to estimate one or more parameters of the atmospheric model, using at least the double difference in altitude as an input to the Kalman filter.

2. The navigation receiver of claim 1, wherein the microprocessor is further configured to:

determine whether the vertical pseudorange residue exceeds a threshold; and

suspend the Kalman filter, if the vertical pseudorange residue is determined to exceed the threshold, to prevent updating the atmospheric model.

3. The navigation receiver of claim 1, further comprising:

an altitude Kalman filter coupled to the pressure sensor and the GNSS receiver, wherein the altitude Kalman filter comprises a first input port coupled to the pressure sensor signal, a second input port coupled to the pseudoranges, and a first output port for providing an altitude signal; and

a horizontal Kalman filter coupled in series to the altitude Kalman filter, wherein the horizontal Kalman filter comprises a first input port coupled to the altitude signal, and an output port for providing a longitude and a latitude.

4. The navigation receiver of claim 3, wherein the altitude Kalman filter further comprises a second output port for providing a clock error and the horizontal Kalman filter further comprises a second input port coupled to the clock error.

5. The navigation receiver of claim 4, wherein the clock error comprises a local clock bias.

6. The navigation receiver of claim 4, wherein the altitude Kalman filter further comprises a third output port for providing a pseudorange offset per satellite and the horizontal Kalman filter further comprises a third input port coupled to the pseudorange offset per satellite.

7. The navigation receiver of claim 3, wherein the altitude Kalman filter further comprises a second output port for providing a pseudorange offset per satellite and the horizontal Kalman filter further comprises a second input port coupled to the pseudorange offset per satellite.

8. A method in a navigation receiver comprising:

providing a pressure sensor signal from a pressure sensor;

providing pseudoranges from a GNSS receiver;

computing (1) a GNSS altitude and a vertical pseudorange residue derived from the pseudoranges, (2) a barometric altitude derived from the pressure sensor signal, based on an atmospheric model, and (3) a double difference in altitude based on a difference between a GNSS altitude variation and a barometric altitude difference; and

estimating, with a Kalman filter, one or more parameters of the atmospheric model, using at least the double difference in altitude as an input to the Kalman filter.

9. The method of claim 8, further comprising:

determining whether the vertical pseudorange residue exceeds a threshold; and

suspending the Kalman filter, if the vertical pseudorange residue is determined to exceed the threshold, to prevent updating the atmospheric model.

10. The method of claim 8, further comprising:

Kalman filtering, with an altitude Kalman filter, the pressure sensor signal from a first input port and the pseudoranges from a second input port to provide an altitude signal from a first output port; and

Kalman filtering, with a horizontal Kalman filter coupled in series with the altitude Kalman filter, the altitude signal from a first input port to provide a longitude and a latitude at an output port.

11. The method of claim 10, further comprising:

generating a clock error from a second output port of the altitude Kalman filter; and

receiving the clock error at a second input port of the horizontal Kalman filter.

12. The method of claim 11, wherein the clock error comprises a local clock bias.

13. The method of claim 11, further comprising:

generating a pseudorange offset per satellite from a third output port of the altitude Kalman filter; and

receiving the pseudorange offset per satellite from a third input port of the horizontal Kalman filter.

14. The method of claim 10, further comprising:

generating a pseudorange offset per satellite from a second output port of the altitude Kalman filter; and

receiving the pseudorange offset per satellite from a second input port of the horizontal Kalman filter.

15. A navigation receiver comprising:

means for providing a pressure sensor signal;

means for providing pseudoranges;

means for computing (1) a GNSS altitude and a vertical pseudorange residue derived from the pseudoranges, (2) a barometric altitude derived from the pressure sensor signal, based on an atmospheric model, and (3) a double difference in altitude based on a difference between a GNSS altitude variation and a barometric altitude difference; and

mean for estimating, with a Kalman filter, one or more parameters of the atmospheric model, using at least the double difference in altitude as an input to the Kalman filter.

16. The navigation receiver of claim 15, further comprises:

means for determining whether the vertical pseudorange residue exceeds a threshold; and

means for suspending the Kalman filter, if the vertical pseudorange residue is determined to exceed the threshold, to prevent updating the atmospheric model.

17. The navigation receiver of claim 15, further comprising:

means for altitude Kalman filtering the pressure sensor signal and the pseudoranges to provide an altitude signal; and

means for horizontal Kalman filtering, with a horizontal Kalman filter coupled in series with an altitude Kalman filter, the altitude signal to provide a longitude and a latitude.

18. The navigation receiver of claim 17, further comprising:

means for generating a clock error from the means for altitude Kalman filtering; and

means for receiving the clock error from the means for horizontal Kalman filtering.

19. The navigation receiver of claim 18, wherein the clock error comprises a local clock bias.

20. The navigation receiver of claim 18, further comprising:

means for generating a pseudorange offset per satellite from the means for altitude Kalman filtering; and

means for receiving the pseudorange offset per satellite from the means for horizontal Kalman filtering.

21. The navigation receiver of claim 17, further comprising:

means for generating a pseudorange offset per satellite from the means for altitude Kalman filtering; and

means for receiving the pseudorange offset per satellite from the means for horizontal Kalman filtering.

22. A non-transitory machine-readable medium comprising software instructions for a navigation receiver, the software instructions comprising code to:

provide a pressure sensor signal from a pressure sensor;

provide pseudoranges from a GNSS receiver;

compute (1) a GNSS altitude and a vertical pseudorange residue derived from the pseudoranges, (2) a barometric altitude derived from the pressure sensor signal, based on an atmospheric model, and (3) a double difference in altitude based on a difference between a GNSS altitude variation and a barometric altitude difference; and

estimate, with a Kalman filter, one or more parameters of the atmospheric model, using at least the double difference in altitude as an input to the Kalman filter.