Method and system for compensating for soft iron magnetic disturbances in a heading reference system

• US 9,207,079 B2
• Filed: 06/21/2012
• Issued: 12/08/2015
• Est. Priority Date: 06/21/2012
• Status: Active Grant

• Current Assignee: Innovative Solutions and Support Incorporated
• Original Assignee: Innovative Solutions and Support Incorporated
• Inventors: Askarpour, Shahram
• Primary Examiner(s): Nguyen, John Q
• Assistant Examiner(s): WHALEN, MICHAEL F
• Application Number:
  US13/529,894
• Publication Number:
  US 20130345972A1
• Time in Patent Office: 1,265 Days
• US Class Current: 1/1
• CPC Class Codes: G01C 17/38 Testing, calibrating, or compensating of compasses
• CPC Class Codes: G01C 19/36 with north-seeking action by magnetic means, e.g. gyromagnetic compasses
• CPC Class Codes: G01C 21/1654 with electromagnetic compass
• CPC Class Codes: G01C 23/00 Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G01C 25/005 initial alignment, calibration or starting-up of inertial devices

Abstract

A method and system for compensating for significant soft iron magnetic disturbances in a heading reference system, such as an aircraft heading reference system, such as an integrated standby unit; or a vehicle inertial system, provides a heading correction signal to the heading reference system when a detected difference in value between a gyro heading relative to magnetic north and a magnetometer reading during a defined measurement period exceeds a predetermined acceptable threshold value of change, such as one based on the expected gyro drift over that period. Upon receipt of the heading correction signal, the gyro heading is adjusted to maintain an accurate heading relative to true magnetic north. If this threshold value is not exceeded, then the magnetometer reading is used for the heading value. This method is iteratively repeated in order to continually maintain an accurate heading and may be employed for each heading measurement axis.

Claims

1. A method for compensating for soft iron magnetic disturbances in a heading reference system, said system comprising a heading gyro disposed along a heading measurement axis and a magnetometer coupled to said heading gyro for providing an accurate heading relative to magnetic north;

said method comprising the steps of;

detecting changes in said magnetometer due to soft iron magnetic disturbances during a detection period for providing a first detected magnitude of change;

detecting changes in said heading gyro relative to magnetic north during said detection period for providing a second detected magnitude of change;

comparing said first and second detected magnitude of changes for providing a potential difference value of change;

providing a predetermined acceptable threshold value of change based on a gyro drift;

determining if said potential difference value of change exceeds said predetermined acceptable threshold value of change; and

providing a heading correction value to said heading reference system when said potential difference value of change exceeds said predetermined acceptable threshold value of change for enabling adjustment of said heading gyro to maintain said accurate heading in the face of said soft iron magnetic disturbances.

2. The compensation method in accordance with claim 1 further comprising the step of periodically correcting said heading gyro utilizing data provided from said magnetometer.

3. The compensation method in accordance with claim 1 wherein said heading correction value providing step comprises the step of providing said heading correction value only when said potential difference value is on the order of a predetermined expected gyro drift over a period since a last adjustment was made to said heading gyro.

4. The compensation method in accordance with claim 1 wherein said heading reference system comprises an aircraft heading reference system.

5. The compensation method in accordance with claim 4 wherein said aircraft heading reference system comprises an integrated standby unit.

6. The compensation method in accordance with claim 1 wherein said heading reference system comprises a vehicle inertial system.

7. The compensation method in accordance with claim 6 wherein said system is subject to local electric field changes, said compensation method further comprising the step of providing a source of heading to said vehicle inertial system subject to variations resulting from said local electric field changes.

8. The compensation method in accordance with claim 1 wherein said compensation method further comprises blending said heading gyro measurements with said magnetometer measurements, said predetermined acceptable threshold value comprising a gyro error covariance.

9. The compensation method in accordance with claim 8 wherein said blending step further comprises the step of blending said heading gyro measurements with said magnetometer measurement using a Kalman filter.

10. The compensation method in accordance with claim 1 wherein said heading reference system comprises a primary attitude and heading reference system.

11. The compensation method in accordance with claim 1 wherein said heading reference system comprises a secondary attitude and heading reference system.

12. The compensation method in accordance with claim 1 wherein said heading reference system comprises a primary air data and attitude heading reference system.

13. The compensation method in accordance with claim 1 wherein said heading reference system comprises a secondary air data and attitude heading reference system.

14. The compensation method in accordance with claim 1 wherein said heading reference system comprises a primary inertial navigation system.

15. The compensation method in accordance with claim 1 wherein said heading reference system comprises a secondary inertial navigation system.

16. The compensation method in accordance with claim 1 wherein said heading reference system comprises a plurality of heading measurement axes, said heading gyro being disposed along said plurality of heading measurement axes, said method further comprising the step of performing said steps for said plurality of axes for providing said heading correction value for said plurality of axes for maintaining said accurate heading in the face of said soft iron magnetic disturbances.

17. The compensation method in accordance with claim 16 wherein said plurality of axes comprises each of said axes for said heading reference system.

18. The compensation method in accordance with claim 1 further comprising the step of correcting said magnetometer for the effect of soft iron magnetic disturbances utilizing data provided from said heading gyro.

19. The compensation method in accordance with claim 1 wherein said heading correction value providing step correction value providing step comprises the step of providing said heading correction value in accordance with the expression

Heading=fn(GH, MH) for AH=<

k

Heading=GH and MH=MH+AH for AH>

k,

where k is a positive constant derived from expected gyro drift over the period At;

AMH is the change in magnetometer derived heading over the period At;

AGH is the change in gyro derived heading over the period At.

20. The compensation method in accordance with claim 19 wherein said heading reference system comprises an aircraft heading reference system.

21. The compensation method in accordance with claim 20 wherein said aircraft heading reference system comprises an integrated standby unit.

22. The compensation method in accordance with claim 19 wherein said heading reference system comprises a vehicle inertial system.

23. The compensation method in accordance with claim 19 wherein said heading reference system comprises an attitude and heading reference system.

24. The compensation method in accordance with claim 19 wherein said heading reference system comprises an air data and attitude heading reference system.

25. The compensation method in accordance with claim 19 wherein said heading reference system comprises an inertial navigation system.

26. The compensation method in accordance with claim 1 wherein said heading correction value providing step comprises the step of providing said heading correction value in accordance with the expression

Heading=fn(ZGI, Magnetometer data)

If AX>

XKI, XM=XM+AX At

If AY>

YKI, YM=YM+AY At,

where XGI, YGI, ZGI represent change of angle in X, Y, Z axis as derived from gyros in inertial reference and XM, YM, ZM represent X, Y, Z magnetometer readings and XKI, YKI, ZKI represent maximum expected gyro angular rate drift in inertial reference;

AX=Irate of change of XGI−

rate of change of XMI

AY=Irate of change of YGI−

rate of change of YMI

AZ=Irate of change of ZGI−

rate of change of ZMI

Pitch=fn(YGI, Accelerometer data, Magnetometer data)

Roll=fn(XGI, Accelerometer data, Magnetometer data).

27. A heading reference system for compensating for soft iron magnetic disturbances and providing an accurate heading relative to magnetic north, the system comprising:

at least one magnetometer capable of measuring a first magnetic data;

at least one heading gyro capable of measuring a first angle rate data;

an electronic storage device capable of storing the first magnetic data and the first angle rate data; and

a microprocessor coupled to the at least one magnetometer, the at least one heading gyro and the electronic storage device being adapted to;

receive the first magnetic data, the first angle rate data, a second magnetic data and a second angle rate data;

compute a first magnetic magnitude of change between the first and the second magnetic data;

compute a second angle rate magnitude of change between the first and the second angle rate data;

compare a change between the first magnetic magnitude of change and the second angle rate magnitude of change to a threshold value based on a gyro drift;

compute a calibration value for the at least one magnetometer or the at least one heading gyro based on the comparison; and

calibrate the at least one magnetometer or the at least one heading gyro using the calibration value.

28. The system in accordance with claim 27 wherein the second magnetic data is used as a heading when the threshold value is not exceeded.

29. The system in accordance with claim 28 wherein computing the first magnetic magnitude of change and the second angle rate magnitude of change happens iteratively.

30. The system in accordance with claim 27 wherein computing the first magnetic magnitude of change and the second angle rate magnitude of change happens iteratively.

31. The system in accordance with claim 30 wherein said heading reference system comprises an aircraft heading reference system.

32. The system in accordance with claim 31 wherein said aircraft heading reference system comprises an integrated standby unit.

33. The system in accordance with claim 27 wherein said heading reference system comprises an aircraft heading reference system.

34. The system in accordance with claim 33 wherein said aircraft heading reference system comprises an integrated standby unit.

35. The system in accordance with claim 27 wherein said heading gyro comprises a triaxial heading gyro disposed along each heading measurement axis, and said magnetometer comprises a triaxial magnetometer.

36. The system in accordance with claim 35 wherein the calibration value is computed for each of the measurement axes.