SYSTEMS AND METHODS FOR DETERMINING LOCATION INFORMATION USING DUAL FILTERS

• US 20090276155A1
• Filed: 04/30/2008
• Published: 11/05/2009
• Est. Priority Date: 04/30/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Liu, Fan, Jeerage, Mahesh
• Granted Patent: US 8,260,552 B2
• Time in Patent Office: Days
• US Class Current: 701/214
• CPC Class Codes: G01S 19/15 Aircraft landing systems
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G01S 19/47 the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled

Abstract

System and methods of increasing reliability of determined location information by using two integration filters are provided. An exemplary embodiment integrates inertial navigation system information and global navigation satellite system (GNSS) information in a real time Kalman filter; determines a real time location of the aircraft with the real time Kalman filter based upon the INS information and the GNSS information; delays the GNSS information by an interval; integrates the INS information and the delayed GNSS information in a delay Kalman filter; determines a predictive location of the aircraft with the delay Kalman filter based upon the INS information, the delayed GNSS information, and the interval; and in response to an inaccuracy of the real time location determined from the real time Kalman filter, selects the predictive location determined from the delay Kalman filter as a new real time location of the aircraft.

Claims

1. A method for determining a real time location of a aircraft, comprising:

receiving inertial navigation system information and global navigation satellite system (GNSS) information with a real time Kalman filter;

determining the real time location of the aircraft with the real time Kalman filter based upon the inertial navigation system information and the GNSS information;

delaying the GNSS information by an interval;

receiving the inertial navigation system information and the delayed GNSS information with a delay Kalman filter;

determining a predictive location of the aircraft with the delay Kalman filter based upon the inertial navigation system information, the delayed GNSS information, and the interval; and

in response to an inaccuracy of the real time location determined from the real time Kalman filter, selecting the predictive location determined from the delay Kalman filter as a new real time location of the aircraft.

2. The method of claim 1, wherein determining the predictive location of the aircraft further comprises:

forward estimating the delayed GNSS information by the interval.

3. The method of claim 1, further comprising:

comparing the predictive location and the real time location; and

determining the inaccuracy of the real time location when a difference between the real time location and the predictive location is different by a threshold distance.

4. The method of claim 1, further comprising:

receiving information from a remote source, the information indicating the inaccuracy of the real time location.

5. The method of claim 4, wherein the remote source is a satellite based augmentation system.

6. The method of claim 4, wherein the remote source is a ground based augmentation system.

7. The method of claim 1, further comprising:

receiving the information indicating the inaccuracy of the real time location from a GNSS receiver.

8. The method of claim 1, further comprising:

outputting one of the real time location and the new real time location to at least one of a flight management system and an auto pilot system.

9. A system that determines a real time location of a aircraft, comprising:

a real time filter operable to receive first location information from an inertial navigation system, operable to receive second location information from a global navigation satellite system (GNSS) receiver, and operable to determine real time location information of the aircraft based upon the inertial navigation system information, the delayed GNSS information, and the interval;

a time interval unit operable to receive the second location information from the GNSS receiver, and operable to delay the received second location information by a time interval;

a delay filter communicatively coupled to the time interval unit, operable to receive from the inertial navigation system the first location information, operable to receive from the time interval unit the second location information delayed by the interval, and operable to determine predictive location information of the aircraft based upon the first location information, the second location information delayed by the interval, and the interval; and

an airborne GNSS device operable to identify a corruption of the second location information, and in response to determining that the second location information is corrupted, is further operable to cause the predictive location information to be output to at least one of a flight management system and an auto pilot system.

10. The system of claim 9, wherein the real time filter is a Kalman filter.

11. The system of claim 9, wherein the delay filter is a Kalman filter.

12. The system of claim 9, wherein the delay filter is operable to forward estimate the second location information by the interval.

13. The system of claim 9, where in response to the airborne GNSS device determining that the second information is not corrupted, the real time location information is communicated to the at least one of the flight management system and the auto pilot system.

14. The system of claim 9, further comprising:

a switch unit communicatively coupled to the real time filter, coupled to the delay filter, and coupled to at least one of the flight management system and the auto pilot system, and operable to be controlled by the airborne GNSS device,

where in response to corruption of the second location information, the switch unit communicates the predictive location information to at least one of the flight management system and the auto pilot system.

15. The system of claim 11, where in response to determining no corruption of the real time location information, the switch unit communicates the real time location information to at least one of the flight management system and the auto pilot system.

16. The system of claim 9, further comprising:

the inertial navigation system system communicatively coupled to the real time filter and the delay filter.

17. The system of claim 9, further comprising:

the GNSS receiver communicatively coupled to the real time filter and the time interval unit, and operable to determine the second location information of the aircraft based upon measurement information from a plurality of satellite signals emitted by a plurality of GNSS satellites, and operable to output the second location information.

18. The system of claim 9, further comprising:

a processor system operable to compare the real time location information and the predictive location information, and operable to determine that the real time location information is corrupted when a difference between the real time location information and the predictive location information is different by a threshold.