Wind estimation for an unmanned aerial vehicle

• US 8,219,267 B2
• Filed: 05/27/2010
• Issued: 07/10/2012
• Est. Priority Date: 05/27/2010
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Hamke, Eric E., Enns, Dale F., Loe, Gregory R., Wacker, Roger A., Schubert, Oliver
• Primary Examiner(s): Beaulieu, Yonel
• Application Number:
  US12/789,238
• Publication Number:
  US 20110295569A1
• Time in Patent Office: 775 Days
• Field of Search: 701/1, 701/3, 701/7, 701213-215, 701/220, 701/14, 703/2
• US Class Current: 701/14
• CPC Class Codes: G01P 5/00 Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft application of speed-measuring devices for measuring volume of fluid G01F
• CPC Class Codes: G01P 7/00 Measuring speed by integrating acceleration measuring travelled distance by double integration of acceleration G01C21/16
• CPC Class Codes: G05D 1/0204 to counteract a sudden perturbation, e.g. cross-wind, gust

Abstract

The speed of the wind during operation of a UAV is estimated. In one example the speed of the wind is estimated by modeling an acceleration of an unmanned aerial vehicle (UAV) based on a measured ground speed of the UAV, determining an actual acceleration of the UAV with one or more sensors, and estimating the speed of the wind as an integral of a difference between the modeled acceleration and the actual acceleration.

Claims

1. A method comprising:

modeling an acceleration of an unmanned aerial vehicle (UAV) based at least on a measured ground speed of the UAV;

determining an actual acceleration of the UAV with one or more sensors; and

estimating a speed of the wind as an integral of a difference between the modeled acceleration and the actual acceleration.

2. The method of claim 1, wherein modeling an acceleration of the UAV comprises:

modeling at least one of one or more forces or one or more moments on the UAV based at least on the measured ground speed of the UAV; and

determining the modeled acceleration based at least on the modeled at least one of one or more forces or one or more moments on the UAV and a mass of the UAV.

3. The method of claim 1, wherein determining an actual acceleration of the UAV comprises determining an actual acceleration of the UAV with one or more accelerometers mechanically connected to the UAV.

4. The method of claim 3, wherein at least one of the one or more accelerometers comprises a multi-axis micro-electro-mechanical accelerometer.

5. The method of claim 1, further comprising estimating a true air speed of the UAV as a sum of the estimated wind speed and the measured ground speed of the UAV.

6. The method of claim 5, further comprising controlling a trajectory of the UAV in flight based at least on the estimated true air speed of the UAV.

7. The method of claim 1, further comprising transforming at least one of the modeled acceleration, the actual acceleration, or the estimated wind speed from a first coordinate system to a second coordinate system.

8. The method of claim 7, wherein transforming at least one of the modeled acceleration, the actual acceleration, or the estimated wind speed from a first coordinate system to a second coordinate system comprises transforming at least one of the modeled acceleration or the actual acceleration from a first Cartesian coordinate system to a second Cartesian coordinate system, wherein one of the first or the second Cartesian coordinate systems comprises a coordinate system oriented relative to the UAV.

9. The method of claim 8, wherein transforming at least one of the modeled acceleration or the actual acceleration from a first Cartesian coordinate system to a second Cartesian coordinate system comprises transforming the modeled acceleration from a first Cartesian coordinate system oriented relative to the UAV to a second Cartesian coordinate system oriented relative to at least one of the one or more sensors.

10. The method of claim 8, wherein transforming at least one of the modeled acceleration or the actual acceleration from a first Cartesian coordinate system to a second Cartesian coordinate system comprises transforming the actual acceleration from a first Cartesian coordinate system oriented relative to at least one of the one or more sensors to a second Cartesian coordinate system oriented relative to the UAV.

11. The method of claim 7, wherein transforming at least one of the modeled acceleration, the actual acceleration, or the estimated wind speed from a first coordinate system to a second coordinate system comprises transforming the estimated wind speed from a Cartesian coordinate system to a geographical coordinate system.

12. The method of claim 1, further comprising determining the measured ground speed based on at least one of inertial measurement, Global Positioning System (GPS), altitude, or acceleration data related to the UAV.

13. The method of claim 1, further comprising multiplying the difference between the modeled acceleration and the actual acceleration by a constant gain.

14. The method of claim 13, further comprising determining the gain based on at least one of one or more simulations or one or more tests of the UAV in flight.

15. The method of claim 14, wherein determining the gain comprises:

running one or more linear simulations of the UAV in flight to determine a first set of values for the gain;

running one or more non-linear simulations of the UAV in flight to test each of the values in the first set of values for the gain; and

running one or more test flights of the UAV employing one or more of the values in the first set of values for the gain to determine one value for the gain.

16. An unmanned aerial vehicle (UAV) comprising:

a plurality of sensors mechanically connected to the UAV; and

a processor configured to model an acceleration on the UAV based at least on a ground speed of the UAV measured based on data from at least one of the sensors, determine an actual acceleration of the UAV with at least one of the sensors, and estimate the speed of the wind as an integral of a difference between the modeled acceleration and the actual acceleration.

17. The UAV of claim 16, further comprising the processor configured to estimate the true air speed of the UAV as a sum of the estimated wind speed and the measured ground speed of the UAV.

18. The UAV of claim 16, further comprising the processor configured to transform at least one of the modeled acceleration, the actual acceleration, or the estimated wind speed from a first coordinate system to a second coordinate system.

19. The UAV of claim 16, further comprising the processor configured to determine the measured ground speed based on at least one of inertial measurement, Global Positioning System (GPS), altitude, or acceleration data from the at least one of the sensors.

20. A non-transitory computer-readable storage medium including instructions that, when executed by a programmable processor, cause the programmable processor to:

model an acceleration of an unmanned aerial vehicle (UAV) based at least on a measured ground speed of the UAV;

determine an actual acceleration of the UAV with one or more sensors; and

estimate the speed of the wind as an integral of a difference between the modeled acceleration and the actual acceleration.