Integrated enroute and approach guidance system for aircraft

• US 5,216,611 A
• Filed: 02/08/1991
• Issued: 06/01/1993
• Est. Priority Date: 02/08/1991
• Status: Expired due to Fees

• Current Assignee: Rockwell International Corporation
• Original Assignee: Rockwell International Corporation
• Inventors: McElreath, Kenneth W.
• Primary Examiner(s): Black, Thomas G.
• Application Number:
  US07/652,762
• Time in Patent Office: 844 Days
• Field of Search: 364/427, 364/428, 364/443, 364/449, 364/453, 342/410, 342/413
• US Class Current: 701/221
• CPC Class Codes: G01C 21/1652 with ranging devices, e.g. LIDAR or RADAR
• CPC Class Codes: G01S 19/15 Aircraft landing systems
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled

Abstract

Data from long range aids such as the global positioning system (GPS) and an inertial navigation system (INS) and short range aids such as a microwave landing system (MLS) are used to smoothly and automatically transition an aircraft from the long range aids to the short range aids. During cruise a Kalman filter combines data from the global positioning system and the inertial navigation system to provide accurate enroute information. When the aircraft arrives in the vicinity of the airport and begins to acquire valid data from the microwave landing system, the Kalman filter is calibrated with the MLS data to permit Precision landing with GPS/INS data alone in case the MLS system subsequently fails. In addition, navigation information begins to be derived from a weighted sum of the GPS/INS and MLS data, the weighting being determined by distance from the airport. In a first region farthest from the airport, the GPS/INS data is given a 1.0 weighting factor; and in a second region nearest the airport, the MLS data is given a 1.0 weighting factor. In a third region intermediate the first and second regions, the GPS/INS data and MLS data are proportionately and complementarily weighted as a function of the distance from the airport. If the MLS system fails, the weighting system is disabled and navigation data is again derived from the GPS/INS combination. In addition, the data from both systems are monitored, and a cockpit alarm is sounded if the data diverges beyond a specified amount.

Claims

1. An integrated system for guiding an aircraft to a predetermined destination, which uses data generated by both a long range navigation system and a short range navigation system, comprising:

means for deriving the data from the long range navigation system;

means for deriving the data from the short range navigation system; and

automatic means for providing a weighted sum of said data from said long range navigation system and said data from said short range navigation system, said sum being weighted as a function of the distance from a predetermined location related to one of each of said long range navigation system or said short range navigation system.

2. An integrated system for guiding an aircraft to a predetermined destination as described in claim 1 wherein said sum is weighted linearly between a first and second distance from said predetermined location.

3. An integrated system for guiding an aircraft to a predetermined destination as described in claim 2 further including means for generating aircraft control data from said data from said long range navigation system and said short range navigation system.

4. An integrated system for guiding an aircraft to a predetermined destination as described in claim 3 further including means for bypassing said providing means when valid data ceases to be derived from said short range navigation transmitter.

5. An integrated system for guiding an aircraft to a predetermined position as described in claim 4 further including:

means for detecting acquisition of valid data from said short range navigation system; and

means responsive to the detecting means for calibrating said data from said long range navigation system.

6. An integrated system for guiding an aircraft to a predetermined destination as described in claim 5 further including means for providing an alert if said data from said short range navigation system diverges from said data from said long range navigation system beyond a predetermined amount.

7. An integrated system for guiding an aircraft to a predetermined destination as described in claim 6 wherein said long range navigation system comprises an inertial navigation system onboard the aircraft and a radionavigation system external to said aircraft and further including means for combining data from the inertial guidance system and data from the radionavigation system.

8. An integrated system for guiding an aircraft to a predetermined destination as described in claim 7 wherein said combining means comprises a Kalman filter.

9. An integrated system for guiding an aircraft to a predetermined destination as described in claim 8 wherein said short range navigation system comprises a microwave landing system.

10. An integrated system for guiding an aircraft to a predetermined destination as described in claim 9 wherein said radionavigation system comprises a global positioning system.

11. An integrated system for guiding an aircraft to a predetermined destination which uses data generated by both a first navigation system having a broad coverage and a second navigation system having coverage in the vicinity of the predetermined destination, comprising:

means for deriving the data from the first navigation system;

means for deriving the data from the second navigation system;

first means for selectively gating said data from said second navigation system;

means for handling said data from said first navigation system;

means for generating a weighted sum of said data from said first navigation system and said data from said second navigation system, said weight being a function of the distance from a predetermined location related to said second navigation system;

second means for selectively gating data either from said handling means or from said generating means; and

means for generating aircraft control data from said data from said long range navigation system and said short range navigation system.

12. An integrated system for guiding an aircraft to a predetermined destination as described in claim 11 wherein said generating means comprises:

first means for weighting said data from one of either said first or said second navigation systems;

second means for weighting said data from the other of said first or said second navigation systems, said first and second weighting means having complementary weighting functions; and

means for summing weighted data from the first and second weighting means.

13. An integrated system for guiding an aircraft to a predetermined destination as described in claim 11 wherein said first selective gating means provides said data from second navigation system upon initial acquisition of valid data from said second navigation system.

14. An integrated system for guiding an aircraft to a predetermined destination as described in claim 13 wherein said second selective gating means ceases to provide data from said generating means upon loss of valid data from said second navigation system.

15. An integrated system for guiding an aircraft to a predetermined destination as described in claim 14 further including means for calibrating said data from said first navigation system upon acquisition of valid data from said second navigation system.

16. An integrated system for guiding an aircraft to a predetermined destination as described in claim 15 wherein said means for deriving said data from said first navigation system includes a Kalman filter.

17. An integrated system for guiding an aircraft to a predetermined destination as described in claim 16 wherein said first navigation system comprises an inertial navigation system onboard the aircraft and a radionavigation system external to said aircraft and further including means for deriving said data from said first navigation system.

18. An integrated system for guiding an aircraft to a predetermined destination as described in claim 17 wherein said second navigation system comprises a microwave landing system.

19. An integrated system for guiding an aircraft to a predetermined destination as described in claim 18 wherein said radionavigation system comprises a global positioning system.

20. An integrated system for guiding an aircraft to an airport, which uses data generated by an inertial navigation system, a global positioning system and a microwave landing system, comprising:

means for deriving the data from the inertial navigation system;

means for deriving the data from the global positioning system;

means for combining said data from said inertial navigation system and said global positioning system to provide composite navigation data;

means for deriving the data from the microwave landing system;

first means for weighting either one of said composite data or said microwave landing system data;

second means for weighting the other of the other of said composite data or said microwave landing system data, said first and second weighting means having complementary weighting functions;

said weighting being a function of the distance from a predetermined location related to one of said global positioning system or said microwave landing system;

means for summing data from the first and second weighting means;

first means for selectively gating said microwave landing system data to said second weighting means and said combining means;

second means for selectively gating data either from said combining means or from said summing means; and

means for generating aircraft control data from the data from said data gated by the second gating means.

21. An integrated system for guiding an aircraft to an airport as described in claim 20 wherein said combining means comprises a Kalman filter.

22. An integrated system for guiding an aircraft to an airport as described in claim 21 wherein said first gating means begins gating said microwave landing system when valid microwave landing system data is received.

23. An integrated system for guiding an aircraft to an airport as described in claim 22 further including means for calibrating said Kalman filter when said microwave landing system data is initially gated by said first gating means.

24. An integrated system for guiding an aircraft to an airport as described in claim 23 wherein said second gating means ceases to gate data when valid microwave landing system data ceases to be received.