Ground proximity warning system with time based mode switching

• US 4,495,483 A
• Filed: 04/30/1981
• Issued: 01/22/1985
• Est. Priority Date: 04/30/1981
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc.
• Original Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Bateman, Charles D.
• Primary Examiner(s): Groody, James J.
• Application Number:
  US06/259,131
• Time in Patent Office: 1,363 Days
• Field of Search: 340/27 R, 340/27 NA, 340/27 AT, 73/178 R, 73/178 T, 244/180, 244/183, 244/181, 244/175, 364/427, 364/433, 343/7 TA, 343/112 A, 343/112 CA
• US Class Current: 340/970
• CPC Class Codes: G01C 5/005 altimeters for aircraft G01C5/02, G01C5/06 take precedence

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 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 time in order to, for example, increase the altitude above ground as a function of time from take-off that a terrain clearance warning may be generated or to decrease as a function of time, the radio altitude below which a negative take-off after a climb warning may be 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 time;

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

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

means responsive to said time signal for switching from said first warning mode means to said second warning mode means as a function of time.

2. A ground proximity warning system for aircraft comprising:

a source of signals representing aircraft flight parameters;

a source of a signal representing time;

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

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

3. The system of claim 2 wherein said source of flight parameter signals include a source of barometric altitude signals and radio 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 reduces said predetermined radio altitude as a function of time.

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

and said warning signal generating means generates said warning signal when the aircraft is below a predetermined radio altitude and wherein said varying means increases said predetermined radio altitude as a function of time.

5. The system of claim 4 wherein said source of time signal includes means responsive to said radio altitude signal for starting said time signal when the aircraft has exceeded a predetermined minimum altitude.

6. The system of claim 5 wherein said source of flight parameter signals additionally 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 signal starting means responds to said phase of flight signal such that said time signal is started during the take-off phase of flight when the aircraft exceeds said predetermined minimum altitude.

7. The system of claim 4 wherein said source of flight parameter signals includes a source of aircraft configuration signals and said source of time signals includes means responsive to said configuration signals for starting said time signal when the aircraft is in a predetermined configuration.

8. The system of claim 7 wherein one of said configuration signals represents landing gear position and said time signal is started when the landing gear is raised.

9. The system of claim 7 wherein one of said configuration signals represents flap position and said time signal is started when the landing gear is raised.

10. The system of claim 4 wherein said varying means increased said predetermined radio altitude from a minimum altitude to a maximum altitude in a predetermined amount of time.

11. The system of claim 10 wherein said minimum altitude is 50 feet.

12. The system of claim 10 wherein said maximum altitude is 500 feet.

13. The system of claim 10 wherein said source of flight parameter signals also includes a source of airspeed signals and wherein said varying means increases said maximum altitude as a function of increasing airspeed.

14. The system of claim 10 wherein said predetermined amount of time is about 3 minutes.

15. The system of claim 4 wherein said source of flight parameter signals include a source of barometric altitude signals and said warning signal generating means additionally generates 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 additionally reduce said predetermined radio altitude as a function of time.

16. The system of claim 15 wherein the maximum value of said predetermined radio altitude is 1000 feet.

17. The system of claim 15 wherein the time of reduction of said predetermined radio altitude from a maximum to a minimum is about 3 minutes.

18. 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;

a source of a signal representing time;

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

a first warning means responsive to said radio altitude signal, said barometric altitude signal, said time 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 signal to decrease said first predetermined radio altitude as a function of time; 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 signal for increasing said second predetermined radio altitude as a function of time.

19. The system of claim 18 including means responsive to said phase of flight signal for starting said time signal during take-off.

20. The system of claim 19 wherein said second predetermined radio altitude increases to a maximum value of 1000 feet.

21. The system of claim 19 wherein said first predetermined radio altitude has a maximum value of 1000 feet.

22. The system of claim 19 wherein the time from the start of said time signal until said first predetermined radio altitude reaches a minimum is about 3 minutes.

23. The system of claim 18 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.