Global navigation satellite system landing systems and methods

• US 7,373,223 B2
• Filed: 02/13/2004
• Issued: 05/13/2008
• Est. Priority Date: 02/13/2004
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Murphy, Timothy A.
• Primary Examiner(s): Tran; Khoi H.
• Assistant Examiner(s): WEISKOPF, MARIE
• Application Number:
  US10/778,725
• Publication Number:
  US 20050182530A1
• Time in Patent Office: 1,551 Days
• Field of Search: 701/16, 701/4, 701/5, 340/951, 342/33, 342/34
• US Class Current: 701/16
• 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: G01S 19/15 Aircraft landing systems
• CPC Class Codes: G01S 19/48 by combining or switching between position solutions derived from the satellite radio beacon positioning system and position solutions derived from a further system

Abstract

A method and system are provided for performing satellite-supported landings in CAT II/III type landing conditions. An exemplary system includes a communication component, a positioning system, a radar altimeter, and a processor. The communication component receives terrain data information related to an instrument landing approach. The positioning system determines position of the aircraft. The radar altimeter generates altitude information of the aircraft. The processor is coupled to the communication component, the positioning system, and the radar altimeter. The processor determines an aircraft altitude based on the determined position of the aircraft, received terrain data information, and the generated altitude information.

Claims

1. A method for performing instrument landings, comprising:

receiving terrain data information from a ground-based augmentation system, the terrain data information including a height of a final approach segment above ground and a variance parameter to account for possible variations in height due to an approach over water;

determining position of an aircraft, including receiving global positioning information from a global navigation satellite system and receiving a differential global positioning, the position of the aircraft being determined from the global positioning information and the differential global positioning information;

generating altitude information of the aircraft from a radar altimeter; and

determining an aircraft altitude based on the determined position of the aircraft, received terrain data information, and the generated altitude information.

2. The method of claim 1, receiving differential global information includes receiving differential global information from a ground-based augmentation system.

3. The method of claim 2, wherein determining an aircraft altitude includes:

determining aircraft'"'"'s position from the earth'"'"'s center based on the generated altitude information of the aircraft from the radar altimeter and a portion of the received terrain data information.

4. The method of claim 3, wherein the terrain data information includes world geodetic information-84.

5. The method of claim 1, further comprising:

sending the determined aircraft altitude to at least one of an autopilot and one or more aircraft displays.

6. The method of claim 1, wherein the instrument landing approach is at least one of a CAT II and CAT III approach.

7. The method of claim 1, wherein determining an aircraft altitude includes:

identifying a terrain data component of the received terrain data information based on differential global positioning information;

adjusting the generated radar altimeter altitude information based on the determined terrain data; and

determining an aircraft altitude based on the adjusted altitude information.

8. The method of claim 7, wherein determining an aircraft altitude is further based on an altitude component of the differential global positioning information.

9. The method of claim 1, wherein determining an aircraft altitude includes obtaining the solution to a least squares fit based on the generated radar altimeter altitude information, the determined position of the aircraft, pitch, roll, and heading information, at least one of velocity or acceleration information for one or more axis of the aircraft.

10. The method of claim 9, wherein obtaining is perform by a Kalman filter.

11. An apparatus for performing instrument landings1, comprising:

a communication component configured to receive terrain data information related to an instrument landing approach from a ground-based augmentation system, the terrain data information including a height of a final approach segment above ground and a variance parameter to account for possible variations in height due to an approach over water;

a position determination component configured to receive global positioning information from a global navigation satellite system, and differential global positioning information, and to determine a position of an aircraft using the global positioning information and the differential global position information;

an altitude generation component configured to generate altitude information of the aircraft from a radar altimeter; and

a processing component configured to determine an aircraft altitude based on the determined position of the aircraft, received terrain data information, and the generated altitude information.

12. The apparatus of claim 11, wherein the processing component is further configured to determine the aircraft position from the earth'"'"'s center based on the generated altitude information of the aircraft from the radar altimeter and a portion of the received terrain data information.

13. The apparatus of claim 12, wherein the terrain data information includes world geodetic information-84.

14. The apparatus of claim 11, further comprising:

a transmission component configured to send the determined aircraft altitude to at least one of an autopilot and one or more aircraft displays.

15. The apparatus of claim 11, wherein the instrument landing approach is at least one of a CAT II and CAT III approach.

16. The apparatus of claim 11, wherein the processing component is further configured to identify a terrain data component of the received terrain data information based on differential global positioning information;

adjust the generated radar altimeter altitude information based on the determined terrain data; and

determine the aircraft altitude based on the adjusted altitude information.

17. The apparatus of claim 16, wherein the processing component is further configured to determine the aircraft altitude based on an altitude component of the differential global positioning information.

18. The apparatus of claim 11, wherein processing component is further configured to obtain a solution to a least squares fit based on the generated radar altimeter altitude information, the determined position of the aircraft, pitch, roll, and heading information, at least one of velocity or acceleration information for one or more axis of the aircraft.

19. The apparatus of claim 18, wherein the solution to a least squares fit is performed by a Kalman filter.

20. An aircraft system for performing instrument landings, comprising:

a communication component configured to receive terrain data information from a ground-based augmentation system, the terrain data information including a height of a final approach segment above ground and a variance parameter to account for possible variations in height due to an approach over water;

a positioning system configured to receive global positioning information from a global navigation satellite system, and differential global positing information, and to determine position of the aircraft based on the global positioning information and the differential global positioning information;

a radar altimeter configured to generate altitude information of the aircraft; and

a processor coupled to the communication component, the positioning system, and the radar altimeter, the processor being configured to determine an aircraft altitude based on the determined position of the aircraft, received terrain data information, and the generated altitude information.

21. The system of claim 20, wherein the positioning system is further configured to receive the differential global positioning information.

22. The system of claim 21, wherein the processor determines position of the aircraft from the center of the earth based on the generated altitude information of the aircraft from the radar altimeter and a portion of the received terrain data information.

23. The system of claim 22, wherein the terrain data information includes world geodetic information-84.

24. The system of claim 20, further comprising:

a component configured to send the determined aircraft altitude to at least one of an autopilot and one or more aircraft displays.

25. The system of claim 20, wherein the instrument landing approach is at least one of a CAT II and CAT III approach.

26. The system of claim 20, wherein the processor identifies a terrain data component of the received terrain data information based on differential global positioning information, adjusts the generated radar altimeter altitude information based on the determined terrain data, and determines an aircraft altitude based on the adjusted altitude information.

27. The system of claim 26, wherein the processor determines an aircraft altitude based on an altitude component of the differential global positioning information.

28. The system of claim 20, further comprising an inertial system configured to generate at least one of velocity or acceleration information for one or more axis of the aircraft, wherein the processor obtains the solution to a least squares fit based on the generated radar altimeter altitude information, the determined position of the aircraft, pitch, roll, and heading information, and the at least one of velocity or acceleration information for one or more axis of the aircraft.

29. The system of claim 28, wherein the processor obtains the solution using a Kalman filter.