METHOD AND SYSTEM FOR ESTIMATING AND PREDICTING AIRFLOW AROUND AIR VEHICLES

• US 20150377915A1
• Filed: 02/07/2014
• Published: 12/31/2015
• Est. Priority Date: 02/07/2013
• Status: Active Application

• Current Assignee: King Abdullah University of Science and Technology
• Original Assignee: King Abdullah University of Science and Technology
• Inventors: CLAUDEL, Christian, SALAMA, Khaled N., CALO, Victor, GHOMMEM, Mehdi, ESLSHURAFA, Amro, SHAQURA, Mohammad
• Application Number:
  US14/766,346
• Publication Number:
  US 20150377915A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: G01P 13/025 indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
• CPC Class Codes: G01P 5/02 by measuring forces exerted by the fluid on solid bodies, e.g. anemometer

Abstract

A method, system, and sensor for air flow sensing. The system can include a cantilever, a transducer, and a processing module. The method can include measuring beam deflections of one or more cantilevers, extracting information about air flow, and determining one or more of an airspeed, an angle of attack, and a sideslip, based on extracted information. The system and method can exploit nonlinearities in the behavior of the cantilever in fluid flow.

Claims

1. A method for air flow sensing, comprising:

measuring beam deflections of a cantilever;

extracting information about air flow; and

determining one or more of an airspeed, an angle of attack, and a sideslip, from the extracted information.

2. The method of claim 1, further comprising generating calibration data from bending amplitudes or torsion amplitudes of the cantilever, wherein one or more of the bending amplitudes and the torsion amplitudes corresponds to a freestream velocity and the angle of attack, wherein the calibration data is used in the determining step.

3. The method of claim 1, wherein the cantilever comprises a cantilever surface;

wherein measuring beam deflections comprises measuring deformation of the cantilever surface; and

wherein determining the airspeed and the angle of attack comprises an unsteady vortex lattice method, solving beam displacements and rotation, and determining convergence with one or more criteria.

4. The method of claim 3, wherein the unsteady vortex lattice method comprises:

discretizing the cantilever surface into a lattice of vortex rings;

imposing a no-penetration condition at collocation points;

computing velocities;

introducing voracity to wakes;

evaluating pressure at the collocation points; and

integrating over the cantilever surface.

5. The method of claim 1, wherein determining the airspeed and the angle of attack further comprises solving potential flow based on an unsteady vortex lattice method.

6. The method of claim 1, wherein determining the airspeed and the angle of attack are based on a nonlinear displacement beam model.

7. The airflow sensing system of claim 1, further comprising:

measuring deformation of the cantilever surface.

8. The airflow sensing system of claim 7, wherein deformation of the cantilever surface is due to beam displacement or rotation or both.

9. The airflow sensing system of claim 8, further comprising:

iteratively determining whether convergence has been achieved

10. The airflow sensing system of claim 1, further comprising:

iteratively determine whether convergence has been achieved.

11. An airflow sensing system for measuring flight data, comprising:

a cantilever having a cantilever surface, the cantilever being positioned on a surface of a vehicle;

a transducer configured to detected deflections of the cantilever and produce an output based the deflections;

a processing module in communication with the cantilever;

wherein the processing module is calibrated to translate the output from the transducer into one or more of an airspeed, an angle of attack, and a sideslip.

12. The airflow sensing system of claim 11, wherein the cantilever is configured to be supercritical beyond the Hopf bifurcation point for providing a stable response to a disturbance below a flutter boundary.

13. The airflow sensing system of claim 11, further comprising:

at least one more cantilever;

at least one more transducer configured to detected deflections of the at least one more cantilever and produce at least one more output to the processing module.

14. The airflow sensing system of claim 13, wherein the cantilever and the at least one more cantilever comprise a cantilever array.

15. The airflow sensing system of claim 14, wherein the cantilever array is a two-dimensional array with each of the two dimensions less than twenty centimeters.

16. The airflow sensing system of claim 15, wherein each of the two dimensions less than ten centimeters.

17. The airflow sensing system of claim 15, wherein each of the two dimensions less than three centimeters.

18. The airflow sensing system of claim 15, wherein each of the two dimensions less than one centimeter.

19. The airflow sensing system of claim 11, wherein the processing module is configured to determine the airspeed and the angle of attack based on calibration data generated from bending amplitudes and/or torsion amplitudes of the cantilever, wherein one or more of the bending amplitudes and the torsion amplitudes corresponds to a freestream velocity and/or the angle of attack.

20. The airflow sensing system of claim 11, wherein the processing module is configured to measure deformation of the cantilever surface.

21. The airflow sensing system of claim 20, wherein deformation of the cantilever surface includes beam displacement or rotation or both.

22. The airflow sensing system of claim 21, wherein the processing module is configured to iteratively determine whether convergence has been achieved

23. The airflow sensing system of claim 11, wherein the processing module is configured to iteratively determine whether convergence has been achieved.

24. The airflow sensing system of claim 11, wherein the processing module is configured to:

discretize the surface into a lattice of vortex rings;

impose a no-penetration condition at collocation points;

compute velocities;

introduce vorticity to wakes;

evaluate pressure at the collocation points; and

integrate over the surface.

25. The airflow sensing system of claim 11, wherein the cantilever has three mutually orthogonal dimensions, and wherein the longest dimension of the cantilever is less than ten centimeters.

26. The airflow sensing system of claim 11, wherein the longest dimension of the cantilever is less than three centimeters.

27. The airflow sensing system of claim 11, wherein the longest dimension of the cantilever is less than one centimeter.

28. The airflow sensing system of claim 11, wherein the longest dimension of the cantilever is less than one millimeter.