SYSTEMS AND METHODS FOR ATTITUDE FAULT DETECTION IN ONE OR MORE INERTIAL MEASUREMENT UNITS

• US 20160290825A1
• Filed: 12/08/2014
• Published: 10/06/2016
• Est. Priority Date: 10/20/2014
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Brenner, Mats Anders, Morrison, John R.
• Granted Patent: US 9,880,021 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G01S 19/47 the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial
• CPC Class Codes: G01S 19/54 using carrier phase measurements; using long or short baseline interferometry

Abstract

Systems and methods for attitude fault detection in an inertial measurement unit (IMU) are disclosed. In one embodiment, an avionics system comprises: an IMU configured to produce a calculated pitch solution, a calculated roll solution, or both; a monitor coupled to the IMU and configured to produce an estimated pitch solution, an estimated roll solution, or both; a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and a display device communicatively coupled to the comparator; wherein the display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.

Claims

1. An avionics system comprising:

at least one inertial measurement unit configured to produce a calculated pitch solution, a calculated roll solution, or both;

at least one monitor coupled to the at least one inertial measurement unit and configured to produce an estimated pitch solution, an estimated roll solution, or both,

wherein the at least one monitor produces the estimated pitch solution by adding angle of attack data to flight path angle data, and

wherein the at least one monitor produces the estimated roll solution by calculating a double-differencing solution using data from transversely mounted dual global navigation satellite system antennas;

a comparator, wherein the comparator determines the difference between the calculated pitch solution and the estimated pitch solution, the difference between the calculated roll solution and the estimated roll solution, or both; and

at least one display device communicatively coupled to the comparator;

wherein the at least one display device receives a warning message from the comparator when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.

2. The avionics system of claim 1, wherein the pitch threshold is 5 degrees.

3. The avionics system of claim 1, wherein the roll threshold is 10 degrees.

4. The avionics system of claim 1, wherein for each of the at least one inertial measurement units there is a respective monitor of the at least one monitors that is incorporated into each of the least one inertial measurement units.

5. The avionics system of claim 1, wherein for each of the at least one inertial measurement units there is a respective monitor of the at least one monitors that is external to a respective inertial measurement unit and coupled to the respective inertial measurement unit.

6. The avionics system of claim 1, wherein the at least one monitor comprises a single monitor and the single monitor is coupled to all of the at least one inertial measurement units.

7. The avionics system of claim 1, wherein the comparator is included in the at least one monitor.

8. The avionics system of claim 1, wherein the comparator is located external to the at least one monitor.

9. The avionics system of claim 1, wherein the estimated pitch solution includes a fixed offset that is determined by the direction of the body of the aircraft when the angle of attack is zero.

10. A non-transitory computer-readable medium having computer-executable instructions stored thereon which, when executed by one or more processors, cause the one or more processors to perform the steps of:

producing a pitch estimate solution by adding angle of attack data to flight path angle data of an aircraft; and

producing a roll estimate solution by calculating a double-differencing solution using data from transversely mounted dual global navigation satellite system antennas.

11. The non-transitory computer-readable medium of claim 10, further comprising instructions which, when executed by one or more processors, cause the one or more processors to perform the steps of:

determining the difference between a calculated pitch solution and the estimated pitch solution, the difference between a calculated roll solution and the estimated roll solution, or both.

12. The non-transitory computer-readable medium of claim 11, further comprising instructions which, when executed by one or more processors, cause the one or more processors to perform the steps of:

causing a warning message to be sent to a display device when the difference between the calculated pitch solution and the estimated pitch solution is greater than a pitch threshold, or when the difference between the calculated roll solution and the estimated roll solution is greater than a roll threshold, or both.

13. The non-transitory computer-readable medium of claim 12, wherein the pitch threshold is 5 degrees.

14. The non-transitory computer-readable medium of claim 12, wherein the roll threshold is 10 degrees.

15. The non-transitory computer-readable medium of claim 10, wherein the estimated pitch solution includes a fixed offset that is determined by the direction of the body of the aircraft when the angle of attack is zero.

16. A method for attitude fault detection in one or more inertial measurement units, comprising:

determining an estimated pitch solution, an estimated roll solution, or both, wherein the estimated pitch solution is determined by adding angle of attack data to flight path angle data and wherein the estimated roll solution is determined by calculating a double-differencing solution using data from transversely mounted dual global navigation satellite system antennas; and

determining a difference between the estimated pitch solution and a calculated pitch solution, the estimated roll solution and a calculated roll solution, or both; and

sending a warning message to a display device when the difference between the estimated pitch solution and the calculated pitch solution is greater than a pitch threshold, the difference between the estimated roll solution and the calculated roll solution is greater than a roll threshold, or both.

17. The method of claim 16, wherein the pitch threshold is 5 degrees.

18. The method of claim 16, wherein the roll threshold is 10 degrees.

19. The method of claim 16, wherein an inertial measurement unit determines the calculated pitch solution and the calculated roll solution;

wherein a monitor determines the estimated pitch solution and the estimated roll solution; and

wherein the monitor is incorporated into the inertial measurement unit.

20. The method of claim 16, wherein an inertial measurement unit determines the calculated pitch solution and the calculated roll solution;

wherein a monitor determines the estimated pitch solution and the estimated roll solution; and

wherein the monitor is external to the inertial measurement unit and coupled to the inertial measurement unit.