SYSTEMS AND METHODS FOR USING COMPUTER VISION FOR PARAFOIL FLIGHT CONTROL

• US 20160137303A1
• Filed: 06/13/2014
• Published: 05/19/2016
• Est. Priority Date: 06/18/2013
• Status: Abandoned Application

• Current Assignee: Logos Technologies, Inc. (Instem Plc)
• Original Assignee: Logos Technologies, Inc. (Instem Plc)
• Inventors: Pullam, Wade, Baker, Patrick, Fields, Dave, Burns, Bradley, Amouzou, Sllete, Schulz, Bryan, Engier, Jim
• Application Number:
  US14/900,087
• Publication Number:
  US 20160137303A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 17/025 for gliding chutes
• CPC Class Codes: B64D 17/34 adapted to control direction or rate of descent
• CPC Class Codes: G05D 1/105 specially adapted for unpowered flight, e.g. glider, parachuting, forced landing parachutes per se B64D17/00
• CPC Class Codes: G06V 20/56 exterior to a vehicle by using sensors mounted on the vehicle

Abstract

Disclosed herein are systems and methods for using computer vision for parafoil flight control. According to an aspect, a method includes capturing an image of a parafoil including multiple indicator points distributed thereon. The method further includes determining positioning of the indicator points based on the captured image. The method further includes determining a condition of the parafoil based on the positioning of the indicator points. The method further includes controlling flight inputs based on the condition of the parafoil.

Claims

1. A method comprising:

capturing an image of a parafoil including a plurality of indicator points distributed thereon;

determining positioning of the indicator points based on the captured image;

determining a condition of the parafoil based on the positioning of the indicator points; and

controlling flight inputs based on the condition of the parafoil.

2. The method of claim 1, further comprising determining the rigidity of the parafoil based on the positioning of the indicator points.

3. The method of claim 1, further comprising:

determining the positioning of the indicator points over a predetermined period of time; and

calculating a differential yaw rate based on the positioning of the indicator points over the predetermined period of time.

4. The method of claim 1, further comprising calculating a differential yaw based on the positioning of the indicator points.

5. The method of claim 4, further comprising determining wind direction based on the calculated differential yaw and a ground track direction.

6. The method of claim 5, further comprising controlling flight inputs based on the determined wind direction.

7. The method of claim 1, further comprising:

determining the positioning of the indicator points over a predetermined period of time; and

calculating a differential pitch rate based on the positioning of the indicator points over the predetermined period of time.

8. The method of claim 1, further comprising calculating a differential pitch based on the positioning of the indicator points.

9. The method of claim 8, further comprising calculating the lift-to-drag ratio based on the calculated the differential pitch.

10. The method of claim 8, further comprising controlling flight inputs based on the calculated differential pitch.

11. The method of claim 1, further comprising positioning an imaging device substantially near the center of a gondola for capturing the image of the parafoil.

12. The method of claim 1, further comprising determining whether a differential yaw is greater than a predetermined value.

13. The method of claim 12, wherein controlling the flight inputs based on the condition of the parafoil comprises controlling a turning rate of the parafoil in response to determining that the differential yaw is greater than the predetermined value.

14. The method of claim 12, wherein controlling the flight inputs based on the condition of the parafoil comprises controlling a propulsion force for adjusting the turning rate of a coupled gondola in response to determining that the differential yaw is greater than the predetermined value.

15. The method of claim 1, wherein controlling the flight inputs comprises creating a drag force on a first side of the parafoil.

16. The method of claim 4, wherein controlling the differential yaw comprises adjusting a plurality of propulsion forces.

17. The method of claim 6, wherein controlling the differential pitch comprises adjusting at least one propulsion force

18. The method of claim 14, wherein controlling the propulsion force for adjusting the turning rate comprises using a first fan and a second fan for propulsion of the parafoil, and

wherein controlling the flight inputs comprises controlling either the first fan or the second fan.

19. A system comprising:

a parafoil including a plurality of indicator points distributed thereon;

a digital imaging device configured to capture an image of the indicator points;

a computing device comprising at least one processor and memory configured to;

determine positioning of the indicator points based on the captured image;

determine a condition of the parafoil based on the positioning of the indicator points; and

control flight inputs based on the condition of the parafoil.

20. The system of claim 19, wherein the computing device is further configured to determine the rigidity of the parafoil based on the positioning of the indicator points.

21. The system of claim 19, wherein the computing device is further configured to:

determine the positioning of the indicator points over a predetermined period of time; and

calculate a differential yaw rate based on the positioning of the indicator points over the predetermined period of time.

22. The system of claim 19, wherein the computing device is further configured to:

calculate a differential yaw based on the positioning of the indicator points.

23. The system of claim 22, wherein the computing device is further configured to determine wind direction based on the calculated differential yaw and a ground track direction.

24. The system of claim 23, wherein the computing device is further configured to control flight inputs based on the determined wind direction.

25. The system of claim 19, wherein the computing device is further configured to:

determine the positioning of the plurality of indicator points over a predetermined period of time; and

calculate a differential pitch rate based on the positioning of the indicator points over the predetermined period of time.

26. The system of claim 19, wherein the computing device is further configured to:

calculate a differential pitch based on the positioning of the indicator points.

27. The system of claim 26, wherein the computing device is further configured to use the calculated differential pitch to calculate the lift-to-drag ratio.

28. The system of claim 26, wherein the computing device is further configured to control flight inputs based on the calculated differential pitch.

29. The system of claim 19, wherein the digital imaging device is positioned substantially near the center of a gondola.

30. The system of claim 19, wherein the computing device is further configured to determine whether a differential yaw is greater than a predetermined value.

31. The system of claim 30, wherein the computing device is further configured to control a turning rate of the parafoil in response to determining that the differential yaw is greater than the predetermined value.

32. The system of claim 31, further comprising:

at least one fan for propulsion of the parafoil, and

wherein the computing device is further configured to control a plurality of propulsion forces for adjusting the differential yaw.

33. The system of claim 31, further comprising:

at least one propulsion force for propulsion of the parafoil, and

wherein the computing device is further configured to control the at least one propulsion force for adjusting the differential pitch rate.

34. The system of claim 19, wherein the computing device is configured to control the flight inputs to create a drag force on a first side of the parafoil.

35. The system of claim 19, further comprising at least one fan for propulsion of the parafoil.

36. The system of claim 19, further comprising:

a first fan and a second fan for propulsion of the parafoil, and

wherein the computing device is configured to control the flight inputs by controlling either the first fan or the second fan.