Methods and apparatus to detect and correct integrity failures in satellite positioning system receivers

• US 7,501,981 B2
• Filed: 06/08/2006
• Issued: 03/10/2009
• Est. Priority Date: 11/18/2005
• Status: Active Grant

• Current Assignee: Texas Instruments, Inc.
• Original Assignee: Texas Instruments, Inc.
• Inventors: Gilkes, Alan Martin, Rahman, Mohammad Atiqur
• Primary Examiner(s): Tarcza; Thomas H
• Assistant Examiner(s): LIU, HARRY K
• Application Number:
  US11/449,239
• Publication Number:
  US 20070115171A1
• Time in Patent Office: 1,006 Days
• Field of Search: 34235701-357017
• US Class Current: 342/357.58
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment

Abstract

Methods and apparatus to detect integrity failures in satellite position system (SPS) receivers are disclosed. An example method comprises estimating a position fix from a plurality of pseudoranges, computing a zero-mean error vector based upon the position fix; and determining if an integrity failure has occurred based on the zero-mean error vector.

Claims

1. A method comprising:

measuring a plurality of pseudoranges using an antenna;

performing a first position fix iteration using the plurality of measured pseudoranges to form a first measurement error vector;

performing a second position fix iteration using the plurality of measured pseudoranges to form a second measurement error vector;

computing a first mean of the first measurement error vector;

subtracting the first mean from the first measurement error vector to form a first zero-mean error vector;

computing a second mean of the second measurement error vector;

subtracting the second mean from the second measurement error vector to form a second zero-mean error vector;

computing a sum vector of the first and the second zero-mean error vectors; and

determining whether an integrity failure has occurred based on the sum vector.

2. A method as defined in claim 1, further comprising;

computing a magnitude of the sum vector; and

comparing the magnitude to a threshold to determine whether the integrity failure has occurred.

3. A method as defined in claim 1, further comprising:

determining a starting position estimate based upon the second position fix iteration;

measuring a second plurality of pseudoranges using the antenna; and

estimating a first position fix from the second plurality of measured pseudoranges and the starting position estimate.

4. A method as defined in claim 3, wherein the second position fix iteration results in a second position fix, and determining the starting position estimate comprises computing an average of the second position fix and at least one previous position fix.

5. A method as defined in claim 4, wherein the average is at least one of a weighted average or an unweighted average.

6. A method as defined in claim 3, wherein the second position fix iteration results in a second position fix, and determining the starting position estimate comprises:

computing a velocity based on the second position fix and at least one previous position fix; and

computing the starting position estimate based on the computed velocity and the position fix.

7. A method as defined in claim 1, wherein measuring the plurality of pseudoranges using the antenna comprises:

using the antenna to receive a plurality of times from respective ones of a plurality of satellites; and

calculating the pseudoranges from the plurality of received times based upon orbital locations of the plurality of satellites.

8. A method as defined in claim 1, wherein the plurality of measured pseudoranges include at least one of a correlated error or a common mode error.

9. An apparatus comprising:

an antenna to receive a plurality of times from respective ones of a plurality of satellites;

a measurement engine to calculate a plurality of pseudoranges based on the received plurality of times;

a position fix engine to estimate a position fix using the plurality of measured pseudoranges, and to compute a measurement error vector based on the position fix;

computing logic to compute a mean of the measurement error vector;

a summer to subtract the mean from the measurement error vector to form a zero-mean error vector; and

an integrity failure detector to detect an integrity failure based on the zero-mean error vector.

10. An apparatus as defined in claim 9, wherein the integrity failure detector comprises:

an accumulator to compute a vector sum of the zero-mean error vector and a previous sum;

expected value computing logic to compute a magnitude of the vector sum; and

a comparator to compare the magnitude to a threshold.

11. An apparatus as defined in claim 9, further comprising an initial position estimator to estimate a starting position estimate based upon at least two previous position fixes estimated by the position fix engine.

12. An apparatus as defined in claim 9, wherein at least one of the position fix engine, the zero-mean computing logic or the integrity failure detector are implemented by a processor executing machine accessible instructions.

13. An article of manufacture storing machine accessible instructions which, when executed, cause a machine to:

measure a plurality of pseudoranges using an antenna;

estimate a position fix from the plurality of measured pseudoranges;

compute a first measurement error vector based on the position fix and the plurality of measured pseudoranges;

compute a mean of the first measurement error vector;

subtract the mean from the first measurement error vector to form a first zero-mean error vector; and

determine whether an integrity failure has occurred based on the first zero-mean error vector.

14. An article of manufacture as defined in claim 13, wherein the machine accessible instructions, when executed, cause the machine to:

update the position fix based on the plurality of measured pseudoranges and a state vector to form a second measurement error vector;

compute a second zero-mean error vector based upon the second measurement error vector; and

compute a vector sum of the first and the second zero-mean error vectors, wherein determining if an integrity failure has occurred is based on the sum.

15. An article of manufacture as defined in claim 14, wherein the machine accessible instructions, when executed, cause the machine to:

compute a magnitude of the vector sum; and

compare the magnitude to a threshold to determine whether the integrity failure has occurred.

16. An article of manufacture as defined in claim 13, wherein the machine accessible instructions, when executed, cause the machine to:

determine a starting position estimate based upon the position fix;

measure a second plurality of pseudoranges using the antenna; and

estimate a second position fix from the second plurality of measured pseudoranges and the starting position estimate.

17. An article of manufacture as defined in claim 13, wherein the machine accessible instructions, when executed, cause the machine to measure the pseudoranges using the antenna by:

receiving a plurality of times from respective ones of a plurality of satellites via the antenna; and

calculating the pseudoranges from the plurality of received times based upon orbital locations of the plurality of satellites.