Ground proximity warning system with time and altitude based mode switching

• US 4,433,323 A
• Filed: 02/04/1982
• Issued: 02/21/1984
• Est. Priority Date: 02/04/1982
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc.
• Original Assignee: Sundstrand Data Control, Inc.
• Inventors: Grove, Michael M.
• Primary Examiner(s): Groody, James J.
• Application Number:
  US06/345,891
• Time in Patent Office: 747 Days
• Field of Search: 340/27 R, 340/27 AT, 340/27 NA, 244/180, 73/178 R, 73/178 T, 343/7 TA, 343/112 A, 343/112 CA, 364/427, 364/433, 364/428
• US Class Current: 340/970
• CPC Class Codes: G01C 5/005 altimeters for aircraft G01C5/02, G01C5/06 take precedence
• CPC Class Codes: G01S 13/935 for terrain-avoidance

Abstract

To increase the effectivity of warnings and to decrease nuisance warnings in a ground proximity warning system having several modes of operation, the switching from one mode to another is done as a function of radio altitude and time. In addition, in a ground proximity warning system where a warning signal is generated in accordance with a predetermined relationship between flight parameters, one or more of these parameters can be varied as a function of radio altitude and time in order to, for example, increase the altitude above ground as a function of radio altitude and time from take-off that a terrain clearance warning is generated or to decrease as a function of radio altitude and time, the radio altitude below which a negative climb after take-off warning is generated.

Claims

1. A ground proximity warning system for aircraft comprising:

a source of signals representing aircraft flight parameters;

a source of a signal representing aircraft radio altitude;

means responsive to said radio altitude signal for generating a time based altitude signal that increases as a function of increasing radio altitude and time;

a first warning mode means responsive to said flight parameter signals and said radio altitude signal for generating a warning signal in accordance with a first predetermined relationship between flight parameters;

a second warning mode means responsive to said flight parameter signals and said radio altitude signal for generating said warning signal in accordance with a second predetermined relationship between flight parameters; and

means operatively connected to said first and said second warning mode means and responsive to said time based altitude signal for deactivating said first warning mode means.

2. The system of claim 1 wherein said source of flight parameter signals includes a source of barometric altitude signals;

wherein said first warning mode means generates said warning signal according to said first predetermined relationship when the aircraft is descending with respect to barometric altitude below a first predetermined radio altitude; and

wherein said second warning mode means generates said warning signal according to said second predetermined relationship when the aircraft descends below a second predetermined radio altitude.

3. The system of claim 2 wherein said deactivating means deactivates said first warning mode means when said time based altitude signal exceeds a predetermined value.

4. The system of claim 2 wherein said source of flight parameter signals includes a source of signals representing aircraft configuration and wherein said system includes means responsive to said configuration signals for generating a signal indicating that the aircraft is in a take-off phase of flight and means for activating said first warning mode means and said time based altitude signal generating means in response to said take-off signal.

5. The system of claim 4 wherein said activating means is also responsive to said radio altitude signal for starting said time based altitude signal when the aircraft exceeds a predetermined minimum radio altitude.

6. The system of claim 5 wherein said source of flight parameter signals includes a source of airspeed signals and wherein said deactivating means is responsive to said airspeed signal to increase said predetermined value of said time based altitude signal as a function of increasing airspeed.

7. The system of claim 2 including means for varying said second predetermined radio altitude as a function of said time based altitude signal.

8. The system of claim 2 wherein said second predetermined radio altitude is approximately equal to seventy-five percent of the maximum radio altitude achieved by the aircraft.

9. The system of claim 7 including means for switching said second predetermined radio altitude to a value independent of said time based altitude signal when said first warning mode is deactivated.

10. A ground proximity warning system for aircraft comprising:

a source of signals representing aircraft flight parameters;

a source of a signal representing aircraft radio altitude;

means responsive to said radio altitude signal for generating a time based altitude signal that increases as a function of increasing radio altitude and time;

means responsive to said flight parameter signals and said radio altitude signal for generating a warning signal in accordance with a predetermined relationship between said flight parameters and radio altitude; and

means responsive to said time based altitude signal and operatively connected to said warning signal generating means for varying as a function of said time based altitude signal said predetermined relationship.

11. The system of claim 10 wherein said source of flight parameter signals includes a source of barometric altitude signals and said predetermined relationship will result in the generation of said warning signal when the aircraft is descending with respect to barometric altitude when the aircraft is below a predetermined radio altitude and wherein said varying means effectively increases the amount of barometric altitude loss required to generate said warning signal as a function of said time based altitude signal.

12. The system of claim 10 wherein said warning signal generating means generates said warning signal when the aircraft descends below a predetermined radio altitude and wherein said varying means increases said predetermined radio altitude as a function of an increase in said time based altitude signal.

13. The system of claim 10 wherein said time based altitude signal means includes means responsive to said radio altitude signal for starting said time based altitude signal when the aircraft has exceeded a predetermined minimum radio altitude.

14. The system of claim 13 wherein said source of flight parameter signals includes a source of signals representing aircraft configuration and wherein said system includes means responsive to said configuration signals for generating a signal indicating that the aircraft is in a take-off phase of flight and wherein said time based altitude signal starting means responds to said phase of flight signal such that said time based altitude signal is started during the take-off phase of flight when the aircraft exceeds said predetermined minimum altitude.

15. The system of claim 10 wherein said source of flight parameter signals includes a source of aircraft configuration signals and said time based altitude signal means includes means responsive to said configuration signals for starting said time based altitude signal when the aircraft is in a predetermined configuration.

16. The system of claim 15 wherein said time based altitude signal means starts said time based altitude signal in response to both said configuration signal and a predetermined minimum radio altitude.

17. The system of claim 12 wherein said varying means increases said predetermined radio altitude from a minimum altitude to a maximum altitude in response to said time based altitude signal.

18. The system of claim 17 wherein said minimum altitude is 50 feet.

19. The system of claim 17 wherein said maximum altitude is 500 feet.

20. The system of claim 17 wherein said maximum is 1000 feet.

21. The system of claim 17 wherein said source of flight parameter signals includes a source of airspeed signals and wherein said varying means increases said maximum altitude as a function of increasing airspeed.

22. The system of claim 17 wherein said predetermined radio altitude is approximately equal to seventy-five percent of the maximum radio altitude gained by the aircraft.

23. The system of claim 12 wherein said source of flight parameter signals includes a source of barometric altitude signals and said warning signal generating means generates said warning signal when the aircraft is descending with respect to barometric altitude when the aircraft is below a second predetermined radio altitude and wherein said varying means reduces said second predetermined radio altitude as said time based altitude signal increases.

24. The system of claim 10, 11 or 23 wherein time based altitude signal means includes means for integrating said radio altitude signal overtime to generate said time based altitude signal.

25. The system of claim 10, 13, 14, 15, 16, 17, 18, 19, 20, 21 or 22 wherein said time based altitude signal means includes means for multiplying said radio altitude signal by a predetermined gain factor.

26. A ground proximity warning system for aircraft comprising:

a source of signals representing aircraft configurations;

a source of a signal representing radio altitude;

a source of a signal representing barometric altitude;

means responsive to said radio altitude signal for generating time based altitude signals that increases as a function of both time and radio altitude;

means responsive to said configuration signals and said radio altitude signals for generating a signal indicating aircraft phase of flight;

a first warning means responsive to said radio altitude signal, said barometric altitude signal, said time based altitude signal and said phase of flight signal for generating a first warning signal when the aircraft is in a take-off phase of flight and is descending with respect to barometric altitude below a first predetermined radio altitude and including means responsive to said time based altitude signal to effectively decrease said first predetermined radio altitude as a function of said time based altitude signals; and

a second warning means responsive to said radio altitude signal and said time signal for generating a second warning signal when the aircraft descends below a second predetermined radio altitude including means responsive to said time based altitude signals for increasing said second predetermined radio altitude as a function of said time based radio altitude signal.

27. The system of claim 26 including means responsive to said phase of flight signal for starting said time based altitude signals during take-off.

28. The system of claim 26 additionally including a source of a signal representing aircraft speed and means responsive to said speed signal to increase said second predetermined radio altitude as a function of time.

29. The system of claim 28 wherein said second predetermined radio altitude increases to a maximum value of 1000 feet.

30. The system of claim 26 wherein said second warning means includes means for generating said second predetermined radio altitude independent of said time based altitude signal when said time based altitude signal exceeds a predetermined value.

31. The system of claim 30 wherein said first warning means is deactivated when said time based altitude signal exceeds said predetermined value.

32. The system of claim 31 including a source of airspeed signals and means operatively connected to said first and second warning means and responsive to said airspeed signal to increase said predetermined time based altitude signal value as a function of airspeed.