System and method for calibrating on-board aviation equipment

• US 20070191999A1
• Filed: 02/10/2006
• Published: 08/16/2007
• Est. Priority Date: 02/10/2006
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Hunter, Jeffrey, Field, Gene, Richey, Manuel
• Granted Patent: US 7,499,803 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: G01S 19/53 Determining attitude
• CPC Class Codes: G01S 3/023 Monitoring or calibrating

Abstract

A method and system are provided for calibrating on-board aviation equipment. An actual bearing from an aircraft to an automatic direction finder (ADF) station is determined. The aircraft is moved to a plurality of headings. An ADF bearing is determined from the aircraft to the ADF station at each of the plurality of headings. An error between the actual bearing and the ADF bearing at each heading is calculated. Then, an error function as a function of the heading of the aircraft is generated based at least in part on the calculated error.

Claims

1. A method comprising:

determining an actual bearing from an aircraft to an automatic direction finder (ADF) station;

moving the aircraft to a plurality of headings;

determining an ADF bearing from the aircraft to the ADF station at each of the plurality of headings to which the aircraft is moved;

calculating an error between the actual bearing and each of the determined ADF bearings; and

generating an error function based at least in part on the calculated errors.

2. The method of claim 1, wherein the actual bearing is obtained from a ground-based marker.

3. The method of claim 2, wherein said determining of the actual bearing and said determining of the ADF bearing for each respective heading of the aircraft are performed while the aircraft is on the ground.

4. The method of claim 1, wherein the actual bearing is obtained using a Global Positioning Satellite (GPS) system and a navigational database including latitude and longitude coordinates for the ADF station.

5. The method of claim 4, wherein at least two of the headings are in different quadrants of a compass.

6. The method of claim 5, wherein the ADF bearing for each respective heading is obtained with an ADF receiver on-board the aircraft that receives a signal transmitted from the ADF station.

7. The method of claim 6, wherein said calculating the error between the actual bearing and the ADF bearing for each respective heading of the aircraft and said generating the error function are performed by a computing system on-board the aircraft.

8. The method of claim 7, further comprising determining the actual bearing for each respective heading of the aircraft.

9. The method of claim 8, wherein said determining of the actual bearing and said determining of the ADF bearing for each respective heading of the aircraft are performed while the aircraft is in flight.

10. A system for calibrating on-board aviation equipment comprising:

an aircraft; and

a computing system on-board the aircraft configured to;

calculate error between an actual bearing from the aircraft to an automatic direction finder (ADF) station and a plurality of ADF bearings from the aircraft to the ADF station, each ADF bearing being associated with a respective one of a plurality of headings of the aircraft; and

generate an ADF error function based at least in part on the calculated error.

11. The system of claim 10, further comprising an ADF receiver on-board the aircraft and in operable communication with the computing system to receive a signal transmitted by the ADF station.

12. The system of claim 11, further comprising a Global Positioning Satellite (GPS) system on-board the aircraft and in operable communication with the computing system and the ADF receiver.

13. The system of claim 12, further comprising a navigation database on-board the aircraft and in operable communication with the computing system, the ADF receiver, and the GPS system, the navigation database including latitude and longitude coordinates for the ADF station.

14. The system of claim 13, wherein the computing system is further configured to determine the actual bearing using the GPS system and the navigation database.

15. The system of claim 14, wherein the computing system is further configured to determine the ADF bearings using the signal received from the ADF receiver.

16. The system of claim 15, further comprising a compass on-board the aircraft and in operable communication with the computing system.

17. A system for calibrating an automatic direction finder (ADF) receiver comprising:

an aircraft;

an ADF receiver on-board the aircraft to receive a signal transmitted from an ADF station; and

a computing system on-board the aircraft and in operable communication with the ADF receiver, the computing system configured to;

determine an actual bearing from the aircraft to the ADF station;

determine an ADF bearing from the aircraft to the ADF station for each of a plurality of headings of the aircraft using the ADF receiver; and

calculate an error between the actual bearing and the ADF bearing for each of the plurality of headings; and

generate an ADF error function based at least in part on the calculated errors.

18. The system of claim 17, further comprising a Global Positioning Satellite (GPS) system and a navigation database on-board the aircraft and in operable communication with the computing system and the ADF receiver.

19. The system of claim 18, wherein the computing system is further configured to determine the actual bearing using the GPS system and the navigation database.

20. The system of claim 19, wherein the computing system is further configured to determine the ADF bearings using the signal received from the ADF receiver.