System for using differential GPS receivers with autopilot systems for category III precision approaches

• US 5,945,943 A
• Filed: 09/17/1997
• Issued: 08/31/1999
• Est. Priority Date: 09/17/1997
• Status: Expired due to Term

• Current Assignee: Trimble Navigation Limited (Trimble Inc.)
• Original Assignee: Trimble Navigation Limited (Trimble Inc.)
• Inventors: Braisted, Paul, Kalafus, Rudolph M.
• Primary Examiner(s): Hellner, Mark
• Application Number:
  US08/932,323
• Time in Patent Office: 713 Days
• Field of Search: 342/357, 342/33, 342/34, 342/35, 701/213, 701/215
• US Class Current: 342/357.31
• CPC Class Codes: G01S 19/15 Aircraft landing systems
• CPC Class Codes: G01S 19/41 Differential correction, e.g. DGPS [differential GPS]
• CPC Class Codes: G01S 2205/003 for aircraft positioning relative to the ground

Abstract

A precision approach capable dual differential global positioning system (DGPS) receiver avionics system. The system of the present invention includes a first and a second DGPS receiver. The first and second DGPS receivers are both adapted to interface with an autopilot in an aircraft. The DGPS receivers each determine the position of the aircraft as the aircraft proceeds along a flight path. Both DGPS receivers are further adapted to employ carrier aiding to smooth the code phase measurements used in determining the position of the aircraft. Within a predetermined range along the approach path of the aircraft and when the output of the first DGPS receiver and the output of the second DGPS receiver are proximate within a predetermined distance, the DGPS receivers determine a transition point. After the transition point, the DGPS receivers utilize DGPS carrier phase tracking to determine the position of the aircraft relative to its position at the transition point. The low noise characteristics of the carrier phase tracking allows the DGPS receivers to properly interface with the autopilot of the aircraft.

Claims

1. A precision approach capable dual differential global positioning system (DGPS) receiver avionics system, comprising:

a first DGPS receiver adapted to interface with an autopilot of an aircraft, said first DGPS receiver adapted to employ carrier aiding to smooth code-phase pseudorange measurements to determine a first position;

a second DGPS receiver adapted to interface with an autopilot of an aircraft, said second DGPS receiver adapted to employ carrier aiding to smooth code-phase pseudorange measurements to determine a second position;

said first DGPS receiver and said second DGPS receiver adapted to determine a transition point, wherein said first position and said second position are proximate within a predetermined distance at said transition point and said transition point is located within a predetermined range on an approach path; and

said first position and said second position set to an initial position after said transition point, said first DGPS receiver and said second DGPS receiver further adapted to utilize carrier phase tracking based upon said initial position, such that said first position and said second position remain proximate within said predetermined distance and such that said first DGPS receiver and said second DGPS receiver properly interface with said autopilot.

2. The precision approach capable DGPS receiver avionics system of claim 1 further comprising:

said first DGPS receiver and said second DGPS receiver combined into a dual DGPS avionics system such that said avionics system mounts in an ILS standard mounting location and uses ILS standard mounting hardware.

3. The precision approach capable DGPS receiver avionics system of claim 1 further comprising:

said first DGPS receiver adapted to output said first position and said second DGPS receiver adapted to output said second position in an angular format consistent with ILS in order to interface with said autopilot.

4. The precision approach capable DGPS receiver avionics system of claim 1 further comprising:

said first DGPS receiver adapted to track a first carrier phase based position measurement such that a first output to said autopilot exhibits lower noise than a first code phase based position measurement;

said second DGPS receiver adapted to track a second carrier phase based position measurement such that a second output to said autopilot exhibits lower noise than a second code phase based position measurement; and

said first output and said second output proximate within said predetermined distance.

5. The precision approach capable DGPS receiver avionics system of claim 1 further comprising:

said first DGPS receiver and said second DGPS receiver adapted to utilize a differential correction signal from a DGPS reference station.

6. The precision approach capable DGPS receiver avionics system of claim 1 further comprising:

said first DGPS receiver and said second DGPS receiver adapted to utilize signals from a wide area augmentation system satellite.

7. The precision approach capable DGPS receiver avionics system of claim 1, wherein said first DGPS receiver and said second DGPS receiver are certified to a Federal Aviation Administration Category III standard.

8. The precision approach capable DGPS receiver avionics system of claim 1, wherein said initial position is a code phase pseudo range based position.

9. The precision approach capable DGPS receiver avionics system of claim 1, wherein said initial position is coincident with said first position or said second position.

10. A differential global positioning system (DGPS) receiver avionics system, comprising:

a first DGPS receiver, said first DGPS receiver adapted to determine a first position;

a second DGPS receiver, said second DGPS receiver adapted to determine a second position;

said first DGPS receiver and said second DGPS receiver adapted to determine said first position and said second position utilizing code phase-based position measurements, said first DGPS receiver and said second DGPS receiver adapted to track said first position and said second position utilizing carrier phase tracking such that said first position and said second position remain proximate within a predetermined distance; and

said predetermined distance sized such that said first DGPS receiver and said second DGPS receiver properly interface with an autopilot.

11. The DGPS receiver avionics system of claim 10, wherein said first DGPS receiver and said second DGPS receiver are certified to a Category III standard such that said autopilot can interface with said first DGPS receiver and said second DGPS receiver to execute a Category III approach.

12. The DGPS receiver avionics system of claim 10, further comprising:

said first DGPS receiver and said second DGPS receiver combined into a dual DGPS avionics system such that said avionics system mounts in an ILS standard mounting location and uses ILS standard mounting hardware.

13. The DGPS receiver avionics system of claim 10, further comprising:

said first DGPS receiver adapted to output said first position and said second DGPS receiver adapted to output said second position in an angular format in order to interface with said autopilot.

14. The DGPS receiver avionics system of claim 10, further comprising:

said first DGPS receiver adapted to track a first code phase based position measurement using carrier phase tracking such that a first output to said autopilot exhibits lower noise than said first code phase based position measurement;

said second DGPS receiver adapted to track a second code phase based position measurement using carrier phase tracking such that a second output to said autopilot exhibits lower noise than said second code phase based position measurement; and

said first output and said second output proximate within said predetermined distance.

15. The DGPS receiver avionics system of claim 10, further comprising:

said first DGPS receiver and said second DGPS receiver adapted to utilize a differential correction signal from a DGPS reference station.

16. The DGPS receiver avionics system of claim 10, further comprising:

said first DGPS receiver and said second DGPS receiver adapted to utilize a differential correction signal from a wide area augmentation system satellite.

17. A method for using differential global positioning system (DGPS) receivers with an autopilot system of an aircraft in a category III precision approach, wherein both differential carrier phase corrections and differential code phase corrections are available, the method comprising the steps of:

a) determining a first position with a first DGPS receiver via code phase measurement;

b) determining a second position with a second DGPS receiver via code phase measurement;

c) interfacing with an autopilot system of an aircraft such that the first DGPS receiver and the second DGPS receiver provide steering information to said autopilot system;

d) initiating a category III precision approach with said aircraft;

e) transitioning to carrier phase tracking wherein said first position is tracked via carrier phase measurement with said first DGPS receiver and said second position is tracked via carrier phase measurement with said second DGPS receiver such that said first position and said second position remain proximate within a predetermined distance; and

f) comparing said first position and said second position within said autopilot to determine whether said first position and said second position are proximate in excess of said predetermined distance.

18. The method of claim 17, wherein step c) further comprises the steps of:

outputting said first position in an angular format consistent with ILS such that said first DGPS receiver interfaces with said autopilot; and

outputting said second position in angular format such that said second DGPS receiver interfaces with said autopilot.

19. The method of claim 17, wherein step e) further comprises the steps of:

determining whether said aircraft is within a predetermined range along an approach path;

determining whether said first position is proximate within a predetermined distance with said second position when said aircraft is within said predetermined range; and

transitioning to carrier phase tracking when said aircraft is within said predetermined range and said first position is proximate within a predetermined distance with said second position.

20. The method of claim 19, further comprising the steps of:

determining a transition point, wherein said transition point is within said predetermined range and said first position is proximate within a predetermined distance with said second position; and

transitioning to carrier phase tracking at said transition point.