Horizontal miss distance filter system for suppressing false resolution alerts

• US 5,566,074 A
• Filed: 08/07/1995
• Issued: 10/15/1996
• Est. Priority Date: 08/07/1995
• Status: Expired due to Term

• Current Assignee: Mitre Corporation
• Original Assignee: Mitre Corporation
• Inventors: Hammer, Jonathan B.
• Primary Examiner(s): Chin, Gary
• Application Number:
  US08/512,011
• Time in Patent Office: 435 Days
• Field of Search: 364/439, 364/461, 342/29, 342/30, 342/31, 342/32, 342/455, 342/456, 340/961
• US Class Current: 701/301
• CPC Class Codes: G01S 13/70 for range tracking only
• CPC Class Codes: G01S 13/74 Systems using reradiation of radio waves, e.g. secondary radar systems; Analogous systems
• CPC Class Codes: G01S 13/933 of aircraft or spacecraft
• CPC Class Codes: G05D 1/0808 specially adapted for aircraft

Abstract

A horizontal miss distance filter system (220) is provided for inhibiting resolution alert messages from an air traffic alert and collision avoidance system (210) to a pilot'"'"'s display (230). The horizontal miss distance filter employs a parabolic range tracker (10) to derive a range acceleration estimate (11) utilized to discriminate intruder aircraft (110) having non-zero horizontal miss distances. The horizontal miss distance calculated from the range data provided by the parabolic range tracker is compared with a bearing based horizontal miss distance provided by a bearing based tracker (22). The smaller of the two calculated horizontal miss distances defines a projected horizontal miss distance which is compared with a threshold value. Any resolution alert for intruder aircraft whose projected horizontal miss distance is greater than the threshold will be inhibited unless it is determined that the encounter involves a maneuver of one of the aircraft. As many as five maneuver detectors (50, 52, 56, 58 and 64) may be employed to assess whether the encounter involves a maneuver. If any of the maneuver detectors establish the occurrence of a maneuver, then a resolution alert provided from the TCAS system (210) will not be inhibited.

Claims

1. A system for suppressing a false resolution alert message from an air traffic alert and collision avoidance system, comprising:

means for input of a surveillance range measurement of an intruder aircraft from the air traffic alert and collision avoidance system;

range tracking means coupled to said surveillance range measurement input means for determining horizontal miss distances greater than a predetermined value using at least a second derivative of a predicted range of the intruder aircraft, said second derivative of said predicted range of the intruder aircraft being greater than a predetermined first threshold value; and

,

inhibit means coupled to said range tracking means and the air traffic alert and collision avoidance system for inhibiting transmission of a resolution alert message responsive to said determined horizontal miss distance being greater than said predetermined value.

2. The system as recited in claim 1 further comprising threshold modifying means coupled to said range tracking means for modifying said first threshold value responsive to a difference between said surveillance range measurement and a calculated predicted range value.

3. The system as recited in claim 2 further comprising bearing tracking means having a surveillance bearing input coupled to said air traffic alert and collision avoidance system for calculating a bearing based horizontal miss distance.

4. The system as recited in claim 3 where said range tracking means includes an input coupled to said bearing tracking means for input of said bearing based horizontal miss distance, said range tracking means including means for selecting a minimum horizontal miss distance from a comparison of said bearing based horizontal miss distance with a range based horizontal miss distance, said minimum horizontal miss distance being compared with said predetermined value, said inhibit means inhibiting transmission of a resolution alert message responsive to said minimum horizontal miss distance being greater than said predetermined value.

5. The system as recited in claim 4 further comprising maneuver detecting means coupled to said range tracking means and said inhibit means for preventing said inhibition of transmission of a resolution alert message responsive to a determination that an intruder aircraft is changing in either direction or speed.

6. The system as recited in claim 1 where said range tracking means further utilizes said predicted range of the intruder aircraft and a predicted range rate of the intruder aircraft.

7. The system as recited in claim 6 where said range tracking means includes means for modifying said first threshold value responsive to a difference between said surveillance range measurement and said predicted range.

8. The system as recited in claim 7 further comprising bearing tracking means having a surveillance bearing input coupled to said air traffic alert and collision avoidance system for calculating a bearing based horizontal miss distance.

9. The system as recited in claim 8 where said range tracking means includes an input coupled to said bearing tracking means for input of said bearing based horizontal miss distance, said range tracking means including means for selecting a minimum horizontal miss distance from a comparison of said bearing based horizontal miss distance with a range based horizontal miss distance, said minimum horizontal miss distance being compared with said predetermined value, said inhibit means inhibiting transmission of a resolution alert message responsive to said minimum horizontal miss distance being greater than said predetermined value.

10. The system as recited in claim 9 further comprising maneuver detecting means coupled to said range tracking means and said inhibit means for preventing said inhibition of transmission of a resolution alert message responsive to a determination that an intruder aircraft is changing in either direction or speed.

11. The system as recited in claim 10 where said maneuver detecting means includes a first maneuver detector having an input coupled to said range tracking means, said first maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of a third derivative of said predicted range being less than zero.

12. The system as recited in claim 11 where said maneuver detecting means includes a second maneuver detector having an input coupled to said range tracking means, said second maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of said predicted range acceleration being less than a predetermined second threshold value.

13. The system as recited in claim 12 where said maneuver detecting means includes Cartesian tracking means coupled to said air traffic alert and collision avoidance system for calculating a Cartesian coordinate range, a Cartesian coordinate range rate, and a Cartesian coordinate range acceleration.

14. The system as recited in claim 13 where said maneuver detecting means includes a third maneuver detector having an input coupled to said Cartesian tracking means, said third maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of said Cartesian coordinate range acceleration being less than a predetermined third threshold value.

15. The system as recited in claim 14 where said maneuver detecting means includes a fourth maneuver detector having an input coupled to said Cartesian tracking means, said fourth maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of a difference between said Cartesian coordinate range and said surveillance range measurement being less than a predetermined fourth threshold value.

16. The system as recited in claim 15 where said maneuver detecting means includes a fifth maneuver detector having an input coupled to said bearing tracking means, said fifth maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of said bearing based horizontal miss distance being less than a predetermined percentage of said range based horizontal miss distance.

17. The system as recited in claim 16 where said maneuver detecting means includes means for preventing said inhibition of transmission of a resolution alert message responsive to identification of an intruder aircraft as maneuvering by any one of said first, second, third, fourth, and fifth maneuver detectors.

18. The system as recited in claim 1 further comprising bearing tracking means having a surveillance bearing input coupled to said air traffic alert and collision avoidance system for calculating a bearing based horizontal miss distance.

19. The system as recited in claim 18 where said range tracking means includes an input coupled to said bearing tracking means for input of said bearing based horizontal miss distance, said range tracking means including means for selecting a minimum horizontal miss distance from a comparison of said bearing based horizontal miss distance with a range based horizontal miss distance, said minimum horizontal miss distance being compared with said predetermined value, said inhibit means inhibiting transmission of a resolution alert message responsive to said minimum horizontal miss distance being greater than said predetermined value.

20. The system as recited in claim 19 further comprising maneuver detecting means coupled to said range tracking means and said inhibit means for preventing said inhibition of transmission of a resolution alert message responsive to a determination that an intruder aircraft is changing in either direction or speed.

21. The system as recited in claim 20 where said maneuver detecting means includes a maneuver detector having an input coupled to said range tracking means, said maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of a third derivative of said predicted range being less than zero.

22. The system as recited in claim 20 where said maneuver detecting means includes a maneuver detector having an input coupled to said range tracking means, said maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of said predicted range acceleration being less than a predetermined second threshold value.

23. The system as recited in claim 20 where said maneuver detecting means includes Cartesian tracking means coupled to said air traffic alert and collision avoidance system for calculating a Cartesian coordinate range, a Cartesian coordinate range rate, and a Cartesian coordinate range acceleration.

24. The system as recited in claim 23 where said maneuver detecting means includes a maneuver detector having an input coupled to said Cartesian tracking means, said maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of said Cartesian coordinate range acceleration being less than a predetermined third threshold value.

25. The system as recited in claim 23 where said maneuver detecting means includes a maneuver detector having an input coupled to said Cartesian tracking means, said maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of a difference between said Cartesian coordinate range and said surveillance range measurement being less than a predetermined fourth threshold value.

26. The system as recited in claim 20 where said maneuver detecting means includes a maneuver detector having an input coupled to said bearing tracking means, said maneuver detector identifying an intruder aircraft is maneuvering responsive to calculation of said bearing based horizontal miss distance being less than a predetermined percentage of said range based horizontal miss distance.

27. The system as recited in claim 1 further comprising means for compensating an estimated time to a closest point of approach of an intruder aircraft, said compensating means providing a corrected range rate corresponding to an estimated range acceleration applied for a time period established by said estimated time to a closest point of approach.

28. A system for suppressing a false resolution alert message from an air traffic alert and collision avoidance system, comprising:

means for input of a surveillance range measurement of an intruder aircraft from the air traffic alert and collision avoidance system;

range tracking means coupled to said surveillance range measurement input means for determining horizontal miss distances greater than a predetermined value using at least a second derivative of a predicted range of the intruder aircraft, said second derivative of said predicted range of the intruder aircraft being greater than a predetermined first threshold value, said range tracking means including maneuver detecting means for determining that the intruder aircraft is changing in either direction or relative speed and providing a maneuver indication output; and

,

inhibit means coupled to said range tracking means and the air traffic alert and collision avoidance system for inhibiting transmission of a resolution alert message responsive to said determined horizontal miss distance being greater than said predetermined value and an absence of said maneuver indication output.

29. The system as recited in claim 28 where said range tracking means further utilizes said predicted range of the intruder aircraft and a predicted range rate of the intruder aircraft.

30. The system as recited in claim 29 where said range tracking means includes means for modifying said first threshold value responsive to a difference between said surveillance range measurement and said predicted range.

31. A method of detecting that an intruder aircraft is maneuvering in an air traffic alert and collision avoidance system, comprising the steps:

providing measured range values of the intruder aircraft at predetermined time intervals;

calculating a predicted range value based on measured range values;

calculating a third derivative of said predicted range value;

determining an occurrence of a maneuver of the intruder aircraft responsive to said third derivative of said predicted range value being less than zero; and

,

inputting an indication of said determined occurrence of a maneuver of the intruder aircraft to an alert filter system for inhibiting said filter system from suppressing an alert message output relative to the intruder aircraft.

32. The method of claim 31 further comprising the steps of:

calculating a second derivative of said predicted range value; and

,

determining the occurrence of a maneuver responsive to said second derivative of said predicted range value being less than an acceleration threshold value.

33. The method of claim 31 further comprising the steps of:

calculating a predicted range value in a Cartesian coordinate system based on said measured range values;

calculating of a second derivative of said predicted Cartesian coordinate range value; and

,

determining the occurrence of a maneuver responsive to said second derivative of said predicted Cartesian coordinate range value being less than a Cartesian acceleration threshold.

34. The method of claim 33 further comprising the steps of:

calculating a difference between said predicted Cartesian coordinate range value and a corresponding one of said measured range values; and

,

determining the occurrence of a maneuver responsive to said calculated difference being less than a predetermined range difference threshold value.

35. The method of claim 31 further comprising the steps of:

calculating a range based horizontal miss distance from said measured range values;

providing a relative bearing value;

calculating a bearing based horizontal miss distance using said relative bearing value; and

,

determining the occurrence of a maneuver responsive to said bearing based horizontal miss distance being less than a predetermined percentage of said range based horizontal miss distance.

36. A method of suppressing a false resolution alert message from an air traffic alert and collision avoidance system, comprising the steps of:

a) providing a measured range value to an intruder aircraft;

b) calculating a predicted range value, a predicted range velocity value and a predicted range acceleration value based on said measured range value for a predetermined future time interval;

c) comparing said predicted range acceleration value with an acceleration threshold value;

d) if said predicted range acceleration value is less than said acceleration threshold value, proceeding to step (a), otherwise continuing;

e) calculating a projected horizontal miss distance for the intruder aircraft;

f) comparing said projected horizontal miss distance with a distance threshold value;

g) if said projected horizontal miss distance is less than said distance threshold value, proceeding to step (a), otherwise continuing;

h) determining whether there is a change in either of a relative direction or a relative speed of the intruder aircraft to identify a maneuvering condition;

i) if said maneuvering condition is identified, proceeding to step (a), otherwise continuing; and

,

j) inhibiting a resolution alert message from the air traffic alert and collision avoidance system.

37. The method of claim 36 where said step of comparing said predicted range acceleration value with an acceleration threshold value includes the steps of calculating a difference between said measured range value and said predicted range value, and adjusting said acceleration threshold value responsive to said calculated difference being greater than a predetermined value.

38. The method of claim 36 where said step of calculating a projected horizontal miss distance includes the steps of:

a) providing a bearing measurement;

b) calculating a first horizontal miss distance from said predicted range value, said predicted range velocity value and said predicted range acceleration value;

c) calculating the intruder aircraft'"'"'s relative estimated position and estimated velocity in Cartesian coordinates from said bearing measurement;

d) calculating a second horizontal miss distance from said relative estimated position and said estimated velocity;

e) comparing said first horizontal miss distance with said second horizontal miss distance to determine a minimum horizontal miss distance and identifying said minimum horizontal miss distance as said projected horizontal miss distance.

39. The method as recited in claim 38 where said step of determining whether there is a change in either of a relative direction or a relative speed includes the steps of comparing said second horizontal miss distance with said first horizontal miss distance, and identifying said maneuver condition responsive to said second horizontal miss distance being less than a predetermined percentage of said first horizontal miss distance.