SYSTEMS AND METHODS FOR CALIBRATING AND ADJUSTING A HEADING REFERENCE SYSTEM

• US 20170038207A1
• Filed: 09/28/2016
• Published: 02/09/2017
• Est. Priority Date: 03/15/2013
• Status: Active Grant

• Current Assignee: Innovative Solutions and Support Incorporated
• Original Assignee: Innovative Solutions and Support Incorporated
• Inventors: Askarpour, Shahram
• Granted Patent: US 9,921,063 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: G01C 17/38 Testing, calibrating, or compensating of compasses
• CPC Class Codes: G01C 21/20 Instruments for performing navigational calculations G01C21/24, G01C21/26 take precedence
• CPC Class Codes: G01C 25/00 Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass testing, calibrating or compensating compasses G01C17/38

Abstract

Systems and methods of calibrating and adjusting for deviations in a vehicle'"'"'s heading system, such as the attitude heading and reference system of an aircraft or the heading system of a ship, positioned along the Earth'"'"'s surface involve calibrating magnetometers for hard iron and misalignment errors using single heading measurements. This can be accomplished by obtaining both actual and theoretical readings for the magnetometer of the heading system, and comparing these values to obtain calibration values for the heading system. The vehicle may be repositioned, such as to North, South, East, and west magnetic headings, with the procedure repeated at each of these headings, and the calibration values averaged, further increasing the accuracy.

Claims

1. A system for recalibrating an aircraft attitude and reference heading system, the system comprising:

an aircraft;

a memory;

at least one magnetometer coupled to the memory;

a processor coupled to the at least one magnetometer and memory, the processor being configured to;

obtain an actual reading from the at least one magnetometer while the aircraft is stationary and positioned along the Earth'"'"'s surface at a single known magnetic heading;

determine a theoretical reading for the at least one magnetometer at the known magnetic heading;

calculate a recalibrated magnetic gain and offset based, at least in part, on the actual reading and the theoretical reading;

utilize the recalibrated magnetic gain and offset to determine a recalibrated magnetic heading for the aircraft;

determine a misalignment value based, at least in part, on a comparison of the known magnetic heading and the recalibrated magnetic heading; and

utilize the misalignment value to adjust the heading system for misalignment errors.

2. The system of claim 1, wherein the processor is further configured to obtain a set of theoretical magnetic field properties from an online source in order to determine the theoretical reading for the at least one magnetometer.

3. The system of claim 1, wherein the processor is further configured to account for variations in a pitch or roll angle of the aircraft.

4. The system of claim 3, wherein the variations in the pitch or roll angle of the aircraft are caused by surface anomalies.

5. The system of claim 1, wherein the aircraft includes an engine and avionics, and wherein the processor is further configured to obtain the actual reading from the at least one magnetometer while the engine and avionics are running.

6. A system for recalibrating an aircraft attitude and reference heading system, the system comprising:

an aircraft;

a memory;

at least magnetometer coupled to the memory;

a processor coupled to the at least one magnetometer and memory, the processor being configured to;

obtain a plurality of actual readings from the at least one magnetometer while the aircraft is stationary and positioned along the Earth'"'"'s surface at a plurality of corresponding known magnetic headings;

determine a plurality of theoretical readings for the at least one magnetometer at the plurality of corresponding known magnetic headings based, at least in part, on a previously computed attitude value for the aircraft;

calculate a recalibrated magnetic gain and offset based, at least in part, on a comparison between the actual readings and the theoretical readings;

utilize the recalibrated magnetic gain and offset to determine a recalibrated magnetic heading for the aircraft and to recalibrate the heading system for measurement errors;

determine a misalignment value based, at least in part, on a comparison of the known magnetic heading and the recalibrated magnetic heading; and

utilize the misalignment value to adjust the heading system for misalignment errors.

7. The system of claim 6, wherein the processor is further configured to obtain a set of theoretical magnetic field properties from an online source in order to determine the plurality of theoretical readings for the at least one magnetometer.

8. The system of claim 6, wherein the processor is further configured to account for variations in a pitch or roll angle of the aircraft.

9. The system of claim 8, wherein the variations in the pitch or roll angle of the aircraft are caused by surface anomalies.

10. The system of claim 6, wherein the aircraft includes an engine and avionics, and wherein the processor is further configured to obtain the actual reading from the at least one magnetometer while the engine and avionics are running.

11. A method for recalibrating an aircraft attitude and reference heading system comprising at least one magnetometer, the method comprising the steps of:

selectively positioning an aircraft along the Earth'"'"'s surface at a single known magnetic heading;

obtaining an actual reading from the at least one magnetometer at the known magnetic heading while the aircraft is stationary;

determining a theoretical reading for the at least one magnetometer at the known magnetic heading;

calculating a recalibrated magnetic average gain and offset based, at least in part, on the actual reading and the theoretical reading; and

utilizing the recalibrated magnetic gain and offset to recalibrate the heading system for measurement errors.

12. The method of claim 11, further comprising obtaining a set of theoretical magnetic field properties from an online source in order to determine the theoretical reading for the at least one magnetometer.

13. The method of claim 11, further comprising accounting for variations in a pitch or roll angle of the aircraft.

14. The method of claim 13, wherein the variations in the pitch or roll angle of the aircraft are caused by surface anomalies.

15. The method of claim 13, wherein the actual reading from the at least one magnetometer at the known magnetic heading is obtained while an engine and avionics of the aircraft are running.

16. A method for recalibrating an aircraft attitude and reference heading system comprising at least one magnetometer, the method comprising the steps of:

selectively positioning an aircraft along the Earth'"'"'s surface at a single known magnetic heading;

obtaining an actual reading from the at least one magnetometer at the known magnetic heading while the aircraft is stationary;

determining a theoretical reading for the at least one magnetometer at the known magnetic heading;

determining a misalignment value based, at least in part, on a comparison of the known magnetic heading and a magnetic heading computed from the actual readings; and

utilizing the misalignment value to adjust the heading system for misalignment errors.

17. The method of claim 16, wherein utilizing the misalignment value to adjust the heading system for misalignment errors further comprises replacing or reinstalling the at least one magnetometer.

18. The method of claim 16, further comprising obtaining a set of theoretical magnetic field properties from an online source in order to determine the theoretical reading for the at least one magnetometer.

19. The method of claim 16, further comprising accounting for variations in a pitch or roll angle of the aircraft.

20. The method of claim 16, wherein the variations in the pitch or roll angle of the aircraft are caused by surface anomalies.