VEHICLE-BASED AUTOMATIC TRAFFIC CONFLICT AND COLLISION AVOIDANCE

• US 20140019034A1
• Filed: 01/11/2013
• Published: 01/16/2014
• Est. Priority Date: 09/28/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Bushnell, Glenn S.
• Granted Patent: US 8,731,812 B2
• Time in Patent Office: Days
• US Class Current: 701/122
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G08G 5/0052 for cruising combined instruments indicating more than one navigational value G01C23/00
• 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

Systems and methods for providing vehicle-centric collision avoidance are disclosed. An example method includes determining a first flight trajectory for a first aircraft, determining a second flight trajectory for a second aircraft, determining a predicted first distance between the first aircraft and the second aircraft at a first closest point of approach based on the first and second flight trajectories, comparing the predicted first distance to a first separation perimeter layer, the first separation perimeter layer defining a first three-dimensional perimeter based on the first aircraft, determining a first adjustment having a first magnitude from the first flight trajectory when the predicted first distance is within a first perimeter, determining a second adjustment having a second magnitude from the first flight trajectory when the predicted first distance is within a second perimeter different from the first perimeter, and altering the first flight trajectory based on the first or second adjustment.

Claims

1. A method to provide aircraft guidance, comprising:

determining a first flight trajectory for a first aircraft;

determining a second flight trajectory for a second aircraft;

determining a predicted first distance between the first aircraft and the second aircraft at a first closest point of approach based on the first and second flight trajectories;

comparing the predicted first distance to a first separation perimeter, the first separation perimeter to define a first three-dimensional perimeter based on the first aircraft;

determining a first flight trajectory adjustment having a first magnitude from the first flight trajectory when the predicted first distance is within the first separation perimeter;

determining a second flight trajectory adjustment having a second magnitude from the first flight trajectory when the predicted first distance is within a second separation perimeter different from the first separation perimeter; and

altering the first flight trajectory based on the first flight trajectory adjustment or the second flight trajectory adjustment.

2. A method as defined in claim 1, wherein the first separation perimeter defines a first three-dimensional space with respect to the first aircraft.

3. A method as defined in claim 2, wherein the second separation perimeter defines a second three-dimensional space with respect to the first aircraft.

4. A method as defined in claim 3, wherein the second three-dimensional space is smaller than the first three-dimensional space and the second magnitude is greater than the first magnitude.

5. A method as defined in claim 2, wherein the second separation perimeter defines a second three-dimensional space with respect to the second aircraft.

6. A method as defined in claim 1, further comprising determining a predicted time until the first aircraft arrives at the closest point of approach, wherein determining the first flight trajectory adjustment and the second flight trajectory adjustment are based on the predicted time.

7. A method as defined in claim 1, wherein altering the first flight trajectory comprises providing an avoidance command to at least one of a command integration module or a flight control system.

8. A method as defined in claim 7, further comprising applying a weight to the avoidance command based on the first flight trajectory adjustment or the second flight trajectory adjustment.

9. A method as defined in claim 8, wherein the applied weight substantially negates the avoidance command when the first flight trajectory adjustment results in an unsafe flight path.

10. A method as defined in claim 8, wherein the applied weight substantially negates the avoidance command when the first flight trajectory adjustment is negligible relative to the first flight trajectory.

11. A flight control apparatus, comprising:

a trajectory generator to determine a first flight trajectory for a first aircraft and to determine a second flight trajectory for a second aircraft;

a collision avoidance component to;

determine a predicted first distance between the first aircraft and the second aircraft at a first closest point of approach based on the first and second flight trajectories;

compare the predicted first distance to a first separation perimeter, the first separation perimeter to define a first three-dimensional perimeter based on the first aircraft;

determine a first flight trajectory adjustment having a first magnitude from the first flight trajectory when the predicted first distance is within the first separation perimeter; and

determine a second flight trajectory adjustment having a second magnitude from the first flight trajectory when the predicted first distance is within a second separation perimeter different from the first separation perimeter; and

a command integration module to alter the first flight trajectory based on the first flight trajectory adjustment or the second flight trajectory adjustment.

12. A flight control apparatus as defined in claim 11, wherein the first separation perimeter defines a first three-dimensional space with respect to the first aircraft.

13. A flight control apparatus as defined in claim 12, wherein the second separation perimeter defines a second three-dimensional space with respect to the first aircraft.

14. A flight control apparatus as defined in claim 13, wherein the second three-dimensional space is smaller than the first three-dimensional space and the second magnitude is greater than the first magnitude.

15. A flight control apparatus as defined in claim 12, wherein the second separation perimeter defines a second three-dimensional space with respect to the second aircraft.

16. A flight control apparatus as defined in claim 11, wherein the trajectory generator is to determine a predicted time until the first aircraft arrives at the closest point of approach, the collision avoidance component to determine the first flight trajectory adjustment and the second flight trajectory adjustment based on the predicted time.

17. A flight control apparatus as defined in claim 11, wherein the command integration module is to alter the first flight trajectory based on an avoidance command.

18. A flight control apparatus as defined in claim 17, wherein the collision avoidance component is to provide a weight to the avoidance command based on the first magnitude or the second magnitude and the command integration module is to implement the avoidance command based on the weight.

19. A flight control apparatus as defined in claim 11, further comprising a database to store flight path information, wherein the trajectory generator is to determine the first and second flight trajectories based on stored flight path information.

20. A computer readable storage medium, excluding propagating signals, the storage medium comprising computer readable instructions which, when executed, cause a processor to at least:

determine a first flight trajectory for a first aircraft;

determine a second flight trajectory for a second aircraft;

determine a predicted first distance between the first aircraft and the second aircraft at a first closest point of approach based on the first and second flight trajectories;

compare the predicted first distance to a first separation perimeter, the first separation perimeter to define a first three-dimensional perimeter based on the first aircraft;

determine a first flight trajectory adjustment having a first magnitude from the first flight trajectory when the predicted first distance is within the first separation perimeter;

determine a second flight trajectory adjustment having a second magnitude from the first flight trajectory when the predicted first distance is within a second separation perimeter different from the first separation perimeter; and

alter the first flight trajectory based on the first flight trajectory adjustment or the second flight trajectory adjustment.