Position based ground proximity warning system for aircraft

• US 4,567,483 A
• Filed: 12/10/1982
• Issued: 01/28/1986
• Est. Priority Date: 12/10/1982
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Original Assignee: Sundstrand Data Control, Inc. (Rtx Corporation)
• Inventors: Bateman, Charles D., Grove, Michael M., Noland, Lyle J., Ward, Wallace E.
• Primary Examiner(s): Groody, James J.
• Application Number:
  US06/448,862
• Time in Patent Office: 1,145 Days
• Field of Search: 340/963, 340/970, 340/968, 340/969, 340/967, 340/959, 340/977, 343/12 A, 343/7 TA, 244/180, 364/433, 73/178 R, 73/178 T
• US Class Current: 340/970
• CPC Class Codes: G01C 5/005 altimeters for aircraft G01C5/02, G01C5/06 take precedence

Abstract

In order to reduce nuisance warnings and to increase the effectiveness of real warnings produced by a ground proximity warning system, the criteria for generating a warning is varied for certain airport areas to take into account the terrain in those areas. Along with position data, certain flight parameters such as heading, altitude, glideslope and localizer deviation are checked by the system in order to ensure that the aircraft is located in the desired warning modification area. In addition, the ground proximity warning system includes a mechanism for ensuring that the corrected barometric altitude of the aircraft is within acceptable limits.

Claims

1. A ground proximity warning system for aircraft comprising:

a source of signals representing aircraft flight parameters;

warning logic means operatively connected to said source of flight parameter signals for comparing said flight parameter signals and generating a warning signal in response to predetermined relationships between selected flight parameter signals;

a source of position signals representing the position of the aircraft; and

condition logic means operationally connected to said warning logic means and said source of position signals for varying said predetermined relationships when the aircraft is in a predetermined warning location.

2. The system of claim 1 wherein said condition logic means includes key logic means for comparing at least one of said flight parameter signals to a predetermined value when the aircraft is in one of said predetermined warning locations and means for generating an inhibit signal for inhibiting said variation of said predetermined relationships when said compared flight parameter signal is not within specified limits of said predetermined value.

3. The system of claim 1 wherein said source of aircraft flight parameter signals includes a radio altitude signal and a barometric based altitude signal and wherein said condition logic means includes an altitude verification logic means responsive to said radio altitude signal and said position signals for generating an altitude verification logic signal representing a confidence level of said barometric based altitude signal for a specific altitude verification position.

4. The system of claim 3 wherein said altitude verification logic means includes means for combining said radio altitude signal with said barometric based altitude signal to generate a signal representing the elevation of the ground within said altitude verification area.

5. The system of claim 4 wherein said condition logic means include means for inhibiting said variations of said predetermined relationship when said elevation signal is not within predetermined limits.

6. The system of claim 3 wherein said altitude verification logic means includes means for generating a time signal representing time of aircraft travel between said altitude verification position and said predetermined warning location.

7. The system of claim 6 wherein said condition logic means include means responsive to said time signal for inhibiting said variation of said predetermined relationships when said time signal exceeds a predetermined value.

8. The system of claim 2 wherein said source of aircraft signals includes a glideslope deviation signal and said inhibit signal is generated when the glideslope deviation signal exceeds a predetermined glideslope deviation value when the aircraft is in said predetermined warning location.

9. The system of claim 2 wherein said source of aircraft signals include a localizer deviation signal and said inhibit signal is generated when said localizer deviation signal exceeds predetermined limits when the aircraft is in said predetermined warning location.

10. The system of claim 2 wherein said source of aircraft signals includes a heading signal and said inhibit signal is generated when said heading signal deviates from a predetermined heading by a predetermined amount when the aircraft is in said predetermined warning location.

11. The system of claim 2 wherein said source of flight parameter signals includes a course signal and said inhibit signal is generated when said course signal deviates from a predetermined course by a predetermined amount when the aircraft is in said predetermined warning location.

12. The system of claim 2 wherein said source of flight parameter includes a corrected altitude signal and said inhibit signal is generated when said corrected altitude signal is below a predetermined value when the aircraft is in said predetermined warning location.

13. A ground proximity warning system for aircraft comprising:

a source of radio altitude signals;

a source of barometric signals;

a source of glideslope deviation signals;

a source of position signals representing the position of the aircraft;

warning logic means operatively connected to said sources of radio altitude signals, barometric altitude signals and glideslope deviation signals for generating a warning signal in response to predetermined relationships between said radio altitude signals, barometric altitude signals and glideslope deviation signals; and

condition logic means operatively connected to said warning means and said source of position signals for varying one or more of said predetermined relationships when the aircraft is in a predetermined warning location.

14. The system of claim 13 additionally including:

a source of localizer deviation signals;

a source of heading signals; and

wherein said condition logic means includes key logic means operatively connected to said source of localizer glideslope and heading signals for generating an inhibit signal for inhibiting said variation of said predetermined relationships when one or more of said localizer, glideslope and heading signals is not within specified limits of predetermined values for said signals.

15. The system of claim 14 including memory means for storing a set of said predetermined signal values for each of said predetermined warning locations.

16. The system of claim 15 additionally including a source of corrected altitude signals and wherein said key logic means is responsive to said corrected altitude signal for generating said inhibit signal when the aircraft is below a predetermined corrected altitude.

17. The system of claim 16 wherein said condition logic means additionally includes altitude verification means for verifying said corrected altitude signal.

18. The system of claim 17 wherein said altitude verification means includes means responsive to said radio altitude signal along with said corrected altitude signal for generating a signal representing the altitude of the terrain.

19. The system of claim 18 wherein said altitude verification means includes means for comparing said terrain altitude signal to a predetermined value of terrain altitude and means for causing said inhibit signal to be generated when said terrain altitude signal is not within specified limits of said predetermined value of terrain altitude.

20. The system of claim 19 wherein said altitude verification means is responsive to said position signal for verifying said corrected altitude signal for a predetermined verification position.

21. The system of claim 20 wherein said altitude verification means includes means for comparing said radio altitude signal to a predetermined altitude and for generating said inhibit signal if said radio altitude signal is below said predetermined altitude.

22. The system of claim 20 wherein said altitude verification means includes means for generating said inhibit signal when said heading signal is not within specified limits of a predetermined heading signal in said predetermined verification position.

23. The system of claim 18 additionally including a source of QNH/QFE logic signals and a source of runway elevation signals and wherein said altitude verification means includes means for subtracting said runway elevation from said terrain altitude signal.

24. The system of claim 20 wherein said condition logic includes timer means for effectively measuring the time between said predetermined verification position and said predetermined warning location and for generating said inhibit signal if said time exceeds a predetermined amount.

25. An altitude verification system for aircraft comprising:

a source of signals representing the barometric altitude of the aircraft;

a source of radio altitude signals;

combining means for subtracting said radio altitude signal from said barometric altitude signal to generate a terrain altitude signal; and

comparator means operatively connected to said subtracting means for comparing said terrain signal to a predetermined terrain altitude elevation.

26. The system of claim 25 wherein said barometric altitude signal represents the corrected barometric altitude.

27. The system of claim 25 including position determining means for activating said combining and comparator means when the aircraft is in a predetermined verification position.

28. The system of claim 27 additionally including a source of QNH/QFE logic signals and a signal representing runway elevation for a runway associated with said predetermined verification position and wherein said combining means is effective to subtract said runway elevation from said terrain altitude signal when said QNH/QFE logic signal indicates that said corrected altitude signal represents barometric altitude above said runway.

29. The system of claim 25 wherein said combining means includes means for averaging at least three consecutive of said terrain altitude signals together before comparing said average terrain altitude signal to said predetermined terrain altitutde elevation.