Method, apparatus and computer program product for unstabilized approach alerting

• US 20010052562A1
• Filed: 02/02/2001
• Published: 12/20/2001
• Est. Priority Date: 02/03/2000
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Johnson, Steven C., Ishihara, Yasuo, Gremmert, Scott
• Granted Patent: US 7,068,187 B2
• Time in Patent Office: Days
• US Class Current: 244/175
• CPC Class Codes: G05D 1/0676 specially adapted for landing
• CPC Class Codes: G08G 5/025 Navigation or guidance aids radar or analogous systems specially adapted for landing purposes G01S13/913
• CPC Class Codes: G08G 5/045 Navigation or guidance aids, e.g. determination of anti-collision manoeuvers radar or analogous systems specially adapted for anti-collision between aircraft G01S13/933

Abstract

A method, apparatus and computer program product for assisting the pilot of an aircraft in making a go-around decision. Various aircraft parameters are monitored during the approach to land and a risk level assessed. When the risk level exceeds a specified threshold, an alert is provided.

Claims

1. A method for alerting the pilot of an aircraft to a potentially hazardous condition comprising the steps of:

estimating a deceleration required to stop the aircraft on a runway of intended landing;

comparing said deceleration to a maximum deceleration of the aircraft; and

asserting an alert signal when said deceleration is greater than said maximum deceleration.

2. The method of

claim 1

wherein said step of estimating deceleration further includes the step of including a gain factor in said deceleration to account for at least one of a plurality of runway surface conditions.

3. The method of

claim 1

wherein said step of estimating deceleration further includes the step of including a gain factor in said deceleration to account for at least one atmospheric condition.

4. The method of

claim 1

wherein said step of asserting an alert signal includes the step of commanding an autopilot go-around manouevre.

48. The apparatus of

claim 3

8 wherein said parameters include terrain data.

5. A method for alerting the pilot of an aircraft to a potential go-around condition comprising the steps of:

monitoring a plurality of parameters indicative of an unstabilized approach;

assigning a risk of go-around value according to each of said parameters; and

asserting an alert signal when said value exceeds a predetermined threshold amount.

6. The method of

claim 5

wherein said step of monitoring a plurality of parameters includes the step of monitoring a change in a speed of the aircraft.

7. The method of

claim 5

wherein said step of monitoring a plurality of parameters includes the step of monitoring a runway wind condition.

8. The method of

claim 5

wherein said step of monitoring a plurality of parameters includes the step of monitoring a flight path angle of the aircraft.

9. The method of

claim 5

wherein said step of monitoring a plurality of parameters includes the step of monitoring a position of the aircraft.

10. The method of

claim 5

wherein said step of monitoring a plurality of parameters includes the step of monitoring a track of the aircraft.

11. The method of

claim 5

wherein said step of asserting an alert signal comprises the step of commanding an autopilot go-around manouevre.

12. The method of

claim 5

wherein said step of asserting an alert signal further comprises the steps of:

asserting a go-around caution alert signal when said value exceeds a first threshold amount and is less than a second threshold amount; and

asserting a go-around warning signal when said value exceeds said second threshold amount.

13. A method of alerting the pilot of an aircraft to a potential go-around condition comprising the steps of:

monitoring a plurality of parameters indicative of a runway landing length required;

assigning a risk of runway overrun value based on said plurality of parameters; and

asserting an alert signal when said risk value exceeds a predetermined threshold value.

14. The method of

claim 13

wherein said step of monitoring a plurality of parameters includes the step of monitoring a deceleration required to stop the aircraft.

15. The method of

claim 13

wherein said step of monitoring a plurality of parameters includes the step of monitoring a runway surface condition.

16. The method of

claim 13

wherein said step of monitoring a plurality of parameters includes the step of monitoring at least one atmospheric condition.

17. The method of

claim 13

wherein said step of asserting an alert signal further comprises the steps of:

asserting a go-around caution alert signal when said value exceeds a first threshold amount and is less than a second threshold amount; and

asserting a go-around warning signal when said value exceeds said second threshold amount.

18. The method of

claim 13

wherein said step of asserting an alert signal comprises the step of commanding an autopilot go-around manouevre.

19. A computer program product for alerting the pilot of an aircraft to a potentially hazardous condition comprising:

a computer readable storage medium having computer readable program code means embodied in said medium, said computer readable program code means having;

a first computer instruction means for estimating a deceleration required to stop the aircraft on a runway of intended landing;

a second computer instruction means for comparing said deceleration to a maximum deceleration of the aircraft; and

a third computer instruction means for asserting an alert signal when said deceleration is greater than said maximum deceleration.

20. The computer program product of

claim 19

further including a fourth instruction means for asserting an autopilot go-around command when said alert signal is asserted.

21. A computer program product for alerting the pilot of an aircraft to a potential go-around condition comprising:

a computer readable storage medium having computer readable program code means embodied in said medium, said computer readable program code means having;

a first computer instruction means for accessing and monitoring a plurality of parameters indicative of an unstabilized approach;

a second computer instruction means for assigning a risk of go-around value according to each of said parameters; and

a third computer instruction means for asserting an alert signal when said value exceeds a predetermined threshold amount.

22. The computer program product of

claim 21

further comprising a fourth instruction means for asserting an autopilot go-around command when said alert signal is asserted.

23. A computer program product for alerting the pilot of an aircraft to a potential go around condition comprising:

a computer readable storage medium having computer readable program code means embodied in said medium, said computer readable program code means having;

a first computer instruction means for accessing and monitoring a plurality of parameters indicative of a runway landing length required;

a second computer instruction means for assigning a risk of runway overrun value based on said plurality of parameters; and

a third computer instruction means for asserting an alert signal when said risk value exceeds a predetermined threshold value.

24. The computer program product of

claim 23

further including a fourth computer instruction means for asserting an autopilot go-around command when said alert signal is asserted.

25. An apparatus for alerting the pilot of an aircraft to a potential go-around condition comprising:

an input coupled to receive a plurality of parameters useful as indicators of an unstabilized approach;

an output; and

a signal processing device, coupled to said input, and to said output for;

assigning a risk of go-around value according to each of said parameters; and

asserting an alert signal when said value exceeds a predetermined threshold amount.

26. The apparatus of

claim 25

wherein said apparatus comprises an Enhanced Ground Proximity Warning computer.

27. The apparatus of

claim 25

wherein said alert signal further includes signals useful for driving a display.

28. The apparatus of

claim 25

wherein said alert signal further includes an aural alert signal.

29. The apparatus of

claim 25

wherein said parameters include a change in a speed of the aircraft.

30. The apparatus of

claim 25

wherein said parameters include a runway wind condition.

31. The apparatus of

claim 25

wherein said parameters include a flight path angle of the aircraft.

32. The apparatus of

claim 25

wherein said parameters include a position of the aircraft.

33. The apparatus of

claim 25

wherein said parameters include a track of the aircraft.

34. The apparatus of

claim 25

wherein said alert signal comprises an autopilot go-around manouevre command.

35. The apparatus of

claim 25

further including a database of runway data.

36. The apparatus of

claim 25

wherein said parameters include runway data.

37. The apparatus of

claim 25

wherein said parameters include terrain data.

38. An apparatus for alerting the pilot of an aircraft to a potential go-around condition comprising:

an input coupled to receive a plurality of parameters useful as indicative of a runway landing length required;

an output; and

a signal processing device, coupled to said input and to said output, for;

assigning a risk of runway overrun value based on said plurality of parameters; and

asserting an alert signal when said risk value exceeds a predetermined threshold value.

39. The apparatus of

claim 38

wherein said parameters include a deceleration required to stop the aircraft.

40. The apparatus of

claim 38

wherein said parameters include a runway surface condition.

41. The apparatus of

claim 38

wherein said parameters include at least one atmospheric condition.

42. The apparatus of

claim 38

wherein said apparatus comprises an Enhanced Ground Proximity Warning computer.

43. The apparatus of

claim 38

wherein said alert signal further includes signals useful for driving a display.

44. The apparatus of

claim 38

wherein said alert signal further includes an aural alert signal.

45. The apparatus of

claim 38

wherein said alert signal comprises an autopilot go-around manouevre command.

46. The apparatus of

claim 38

further including a database of runway data.

47. The apparatus of

claim 38

wherein said parameters include runway data.

59. The apparatus of

claim 46

wherein said database further includes terrain data.

49. An apparatus for alerting the pilot of an aircraft to a potentially hazardous condition comprising:

an input coupled to receive runway data and at least one aircraft performance data;

an output; and

a signal processing device coupled to said input and to said output for;

estimating a deceleration required to stop the aircraft on a runway of intended landing;

comparing said deceleration to a maximum deceleration of the aircraft; and

asserting an alert signal when said deceleration is greater than said maximum deceleration.

50. The apparatus of

claim 49

wherein said runway data includes at least one runway surface condition.

51. The apparatus of

claim 49

wherein said input is further coupled to receive at least one atmospheric condition.

52. The apparatus of

claim 49

wherein said input is further coupled to receive a runway end point data.

53. The apparatus of

claim 49

wherein said alert signal includes an autopilot go-around manouevre command.

54. The apparatus of

claim 49

wherein said alert signal further includes signals useful for driving a display.

55. The apparatus of

claim 49

wherein said alert signal further includes an aural alert signal.

56. The apparatus of

claim 49

further including a database of runway data.

57. The apparatus of

claim 49

wherein said apparatus comprises an Enhanced Ground Proximity Warning computer.

58. The apparatus of

claim 56

wherein said database further includes terrain data.