Fault detection and exclusion method for navigation satellite receivers

• US 5,808,581 A
• Filed: 12/07/1995
• Issued: 09/15/1998
• Est. Priority Date: 12/07/1995
• Status: Expired due to Term

• Current Assignee: Trimble Navigation Limited (Trimble Inc.)
• Original Assignee: Trimble Navigation Limited (Trimble Inc.)
• Inventors: Braisted, Paul E., Beckmann, Martin
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US08/568,832
• Time in Patent Office: 1,013 Days
• Field of Search: 342/357, 364/449.7, 701/213
• US Class Current: 342/357.58
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment

Abstract

In a GPS navigation satellite receiver, a pseudorange step detection method integrates the pseudorange rates to predict expected changes in the pseudoranges from one measurement to the next. The pseudorange rate is directly measured as the carrier Doppler shift. The pseudorange and pseudorange rate from a last measurement from each satellite and a pseudorange rate from a new measurement are used to estimate the expected pseudorange. Such estimate accounts for vehicle velocity and accelerations. The expected pseudorange is compared to a newly measured pseudorange. An impermissible pseudorange step is declared when the difference exceeds a variable threshold. Tests can be done on measurements taken up to ten seconds apart, e.g., using a threshold of five hundred meters. The maximum position dilution of precision is typically set at a value of twelve. Satellites that manifest a pseudorange step are thereafter excluded from participating in subsequent position solution activity.

Claims

1. A method for pseudorange step detection in a navigation satellite receiver comprising the steps of:

collecting new pseudorange measurements from a plurality of orbiting satellites;

comparing a new pseudorange measurement to an expected pseudorange propagated from a previous code-based pseudorange with an average pseudorange rate obtained from a current and a last carrier Doppler measurement; and

if a difference based on consecutive samples taken not more than ten seconds apart is greater than a threshold distance, an impermissible pseudorange step is declared and further measurements from a particular corresponding satellite are not used in the position computations for about ten minutes.

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

doing an initial integrity check on each of a plurality of position fixes derived from said pseudorange measurements;

whenever an initial integrity check fails, using the navigation satellite receiver in an attempt to find a subset of satellites for which Fault Detection and Exclusion (FDE) is possible without generating an integrity warning;

returning of candidate satellites to a list of available satellites previously excluded by a FDE process;

successively excluding satellites one at a time from said list of available satellites, and rechecking the integrity of each satellite subset produced; and

if a set of satellites is found that passes an integrity check, the excluded satellite remains excluded for a period of time and then is returned to said list of available satellites if it also passes a tracking and availability requirement.

3. The method of claim 2, wherein:

pseudorange measurements for all selected satellites are compared to expected pseudoranges to said orbiting satellites from a user position to determine if a position error is larger than a protection limit.

4. The method of claim 3, further comprising the step of:

reporting the results of any fault detection to a host processor connected to the navigation satellite receiver.

5. The method of claim 2, further comprising the step of:

calculating the difference between an automatic barometric pressure altitude input and an altitude purely obtained from pseudorange measurements from a minimum number of said orbiting satellites.

6. The method of claim 2, further comprising the step of:

correcting a constraint altitude if fault detection is not possible using pseudorange measurements from said orbiting satellites only, thereafter using said altitude for fault detection, weighted with a weighting factor.

7. A navigation satellite receiver with pseudorange step detection, comprising:

a downconverter and demodulator for collecting new pseudorange measurements from a plurality of orbiting satellites;

a microcomputer connected to the downconverter and demodulator for comparing a new pseudorange measurement to an expected pseudorange propagated from a previous code-based pseudorange with an average pseudorange rate obtained from a current and a last carrier Doppler measurement; and

threshold detector connected to the microcomputer for declaring an impermissible pseudorange step if a difference based on consecutive samples taken not more than a period apart is greater than a threshold distance.

8. A navigation satellite receiver with pseudorange step detection, comprising:

a detector providing for checking each measurement from a satellite for a pseudorange step error;

a filter providing for excluding said satellite from use in a position solution activity for a period of time if a pseudorange step error is detected; and

a threshold detector providing for comparing a navigation measurement for each satellite-in-use to an expected value of pseudorange and pseudorange rate from an assumed vehicle position at a measurement time, wherein a difference between a measured and a predicted value is used to update a position estimate and a velocity estimate.

9. A navigation satellite receiver with position solution integrity checking, comprising:

a detector providing for finding a subset of orbiting navigation satellites for which fault detection and exclusion (FDE) is possible without generating an integrity warning whenever an initial integrity check fails;

a first list manager providing for returning of a set of candidate satellites to a list of available satellites previously excluded by a FDE process;

a second list manager providing for successively excluding each of said candidate satellites one at a time from said list of available satellites, and rechecking the integrity of each satellite subset produced; and

a third list manager providing for keeping an excluded satellite excluded if a set of satellites is found that passes an integrity check for a period of ten minutes and for returning said excluded satellite to said list of available satellites if a tracking and availability requirement is satisfied.

10. The receiver of claim 9, wherein:

the detector further provides for pseudorange measurements for all selected satellites to be compared to expected pseudoranges to the satellites from a user position to determine if a position error is larger than a protection limit.

11. The receiver of claim 10, further comprising:

an alarm providing for reporting the results of any fault detection to a host processor connected to the navigation satellite receiver.

12. The receiver of claim 9, further comprising:

a calculator for finding a difference between an automatic barometric pressure altitude input and an altitude purely obtained from a set of pseudorange measurements from a minimum number of satellites.

13. The receiver of claim 9, further comprising:

a processor for correcting a constraint altitude if a fault detection is not possible using pseudorange measurements from orbiting satellites only, and for thereafter using said constraint altitude for fault detection including a weighting factor.