COLLISION AVOIDANCE FOR VEHICLE CONTROL SYSTEMS

• US 20100256909A1
• Filed: 06/18/2004
• Published: 10/07/2010
• Est. Priority Date: 06/18/2004
• Status: Active Grant

• Current Assignee: L3 Technologies, Inc. (L3Harris Technologies, Inc.)
• Original Assignee: L-3 Communications Geneva Aerospace, Inc. (L3Harris Technologies, Inc.)
• Inventors: Duggan, David S., Felio, David A., Askew, Craig S.
• Granted Patent: US 7,818,127 B1
• Time in Patent Office: Days
• US Class Current: 701/301
• CPC Class Codes: G05D 1/106 Change initiated in response to external conditions, e.g. avoidance of elevated terrain or of no-fly zones
• CPC Class Codes: G08G 5/0069 specially adapted for an unmanned aircraft
• CPC Class Codes: G08G 5/0086 for monitoring terrain radar or analogous systems specially adapted for terrain avoidance G01S13/935
• 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 and apparatus for at least semi-autonomously controlling a vehicle so as to avoid collisions are provided. A sensor is utilized to scan an area proximate the vehicle for a potential object of collision. The apparatus calculates navigational states of the potential object of collision relative to the vehicle to determine that the vehicle is on a course to enter within a predetermined miss distance relative to the potential object of collision. The apparatus alters the course of the vehicle based on the calculated navigational states.

Claims

1. A method for autonomously controlling an aircraft so as to avoid collisions, the method comprising:

(a) utilizing a sensor to scan an area proximate the aircraft for a potential object of collision;

(b) utilizing data collected from the sensor to generate a moving object track for the potential object of collision, the moving object track including an elevation direction finding angle and an azimuth direction finding angle for the potential object of collision, the elevation and the azimuth direction finding angles being relative to the sensor;

(c) utilizing an inertial guidance system to determine the position and velocity of the aircraft;

(d) utilizing the elevation direction finding angle, the azimuth direction finding angle, the aircraft position, and the aircraft velocity to estimate a relative range vector ( R), a relative range rate vector ( {dot over (R)}), a line-of-sight angle vector ( λ

), a line-of-sight rate vector ( {dot over (λ

)}), a range magnitude (R), and a range rate ({dot over (R)}) between the potential object of collision and the aircraft;

(e) performing a calculation so as to determine whether the aircraft is on a course to enter within a predetermined distance relative to the potential object of collision, wherein the calculation utilizes the equations;

2. The method of claim 1, wherein altering the course of the aircraft comprises altering the course of the aircraft without affirmation from a pilot.

3. The method of claim 2, further comprising:

comparing the ZEM to a predetermined miss distance limit; and

activating an avoid alert flag upon the ZEM being less than the predetermined miss distance limit.

4. The method of claim 3, further comprising:

deactivating the avoid alert flag upon the ZEM being greater than the predetermined miss distance limit.

7. The method of claim 2, wherein step (f) comprises calculating an acceleration command to accelerate away from the potential object of collision, wherein the acceleration command (n_c) is determined utilizing the equation:

8. The method of claim 2, wherein the relative range vector, the relative range rate vector, the line-of-sight angle vector, and the line-of-sight rate vector between the potential object of collision and the aircraft are computed into local vertical coordinates.

9. The method of claim 8, wherein the local vertical coordinates are based on a North, East, Down reference frame.

10. The method of claim 9, wherein the aircraft is an unmanned aerial vehicle.

27. The method of claim 2 wherein step (a) comprises utilizing a camera to scan an area proximate the aircraft for a potential object of collision and wherein step (b) comprises utilizing video from the camera to generate the moving object track for the potential object of collision.

28. The method of claim 27 wherein step (a) comprises utilizing a visible light wavelength camera and wherein step (b) comprises utilizing real-time video collected from the camera to generate the moving object track.

29. The method of claim 27 wherein step (a) comprises utilizing a non-visible light wavelength camera.

30. The method of claim 2, further comprising:

communicating with a ground control station, wherein communicating with a ground control station comprises alerting an operator that the aircraft is on a course to collide with the potential object of collision.

32. The method of claim 30, wherein communicating with a ground control station comprises relaying information related to the potential object of collision.

33. The method of claim 30, wherein communicating with a ground control station comprises relaying the positional and velocity information of the aircraft.

5-6. -6. (canceled)

11-26. -26. (canceled)

31. (canceled)

34-36. -36. (canceled)

37. A method for autonomously controlling an aircraft so as to avoid collisions, the method comprising:

utilizing a sensor to scan an area proximate the aircraft for a potential object of collision;

utilizing data collected from the sensor to generate a moving object track for the potential object of collision;

determining the position and velocity of the aircraft;

generating a best estimate of the position and velocity of the potential object of collision based at least in part on the moving object track and on the position and velocity of the aircraft;

performing a calculation so as to determine whether the aircraft is on a course to enter within a predetermined distance relative to the potential object of collision, wherein the calculation utilizes the equation;

ZEM= {dot over (λ

)}V_Ct_go²

where ZEM is a closest point of approach vector that the aircraft will be with respect to the potential object of collision, {dot over (λ

)} is a line-of-sight rate vector, V_C is a closing velocity, and t_go is a time-to-go; and

altering the course of the aircraft based at least in part on the calculation.

38. The method of claim 37, further comprising repeating said performing and said altering until the aircraft is on course to not enter within the predetermined distance relative to the potential object of collision.

39. The method of claim 37, wherein performing a calculation comprises calculating that the aircraft is on course to enter into a head-on collision.

40. The method of claim 39, wherein altering the course comprises guiding the aircraft away from the potential object of collision according to civilian aircraft operating rules.

41. The method of claim 40, wherein altering the course comprises calculating a waypoint leg to alter the course of the aircraft.

42. The method of claim 41, further comprising:

restoring a previous course of the aircraft after the aircraft has avoided the potential object of collision.