Methods and apparatus to adjust folding wing tips

• US 10,370,084 B2
• Filed: 07/21/2017
• Issued: 08/06/2019
• Est. Priority Date: 07/21/2017
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Cline, Paul Jay, Agdamag, Arnold F.
• Primary Examiner(s): Lee, Tyler J
• Application Number:
  US15/656,840
• Publication Number:
  US 20190023373A1
• Time in Patent Office: 746 Days
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

Methods and apparatus to adjust folding wing tips are disclosed. A disclosed example apparatus includes an actuator to cause a movement of a folding portion of an aerodynamic structure, where the folding portion has an associated backlash. The example apparatus also includes a sensor to acquire movement data of the folding portion during movement of the folding portion, and a processor to determine a bias of the folding portion based on the movement data to characterize the backlash.

Claims

1. An apparatus comprising:

an actuator to cause a movement of a folding portion of an aerodynamic structure, the folding portion having an associated backlash;

a sensor to acquire movement data of the folding portion during movement of the folding portion;

a position data analyzer to generate histogram data based on the movement data; and

a processor to determine a bias of the folding portion based on the movement data to characterize the backlash.

2. The apparatus as set forth in claim 1, wherein the position data analyzer identifies a peak of the histogram data to determine the bias.

3. The apparatus as set forth in claim 1, wherein the bias includes a hinge line bias or a drive line bias.

4. The apparatus as set forth in claim 1, wherein the sensor is a pressure sensor of a hydraulic system that is operatively coupled to the folding portion.

5. The apparatus as set forth in claim 4, wherein the actuator is to repeat the movement of the folding portion until a change in pressure differential measured at the pressure sensor exceeds a threshold value.

6. The apparatus as set forth in claim 1, wherein the movement is responsive to a triangular waveform.

7. The apparatus as set forth in claim 1, wherein the folding portion includes an aircraft wing tip.

8. A method comprising:

moving, via an actuator, a folding portion of an aerodynamic structure, the folding portion having an associated backlash;

acquiring movement data during the moving of the folding portion;

generating histogram data based on the movement data; and

calculating, via a processor, a bias of the folding portion based on the movement data to characterize the backlash.

9. The method as set forth in claim 8, further including adjusting a calibrated center position of the folding portion based on the calculated bias.

10. The method as set forth in claim 8, wherein the movement data includes position measurements.

11. The method as set forth in claim 8, wherein the movement data includes a change in pressure differential measured at a pressure sensor associated with the actuator.

12. The method as set forth in claim 8, wherein the moving of the folding portion is responsive to a triangular waveform.

13. The method as set forth in claim 8, wherein a peak of the histogram data is identified to calculate the bias.

14. The method as set forth in claim 13, wherein the movement data includes pressure data.

15. A non-transitory computer readable storage medium comprising instructions, which when executed, cause a processor to at least:

generate histogram data based on movement data of a folding portion of an aerodynamic structure; and

determine a bias of the folding portion based on the movement data of the folding portion to characterize a backlash associated with the folding portion.

17. The non-transitory computer readable storage medium as defined in claim 15, wherein the bias is determined based on identifying a peak of the histogram data.

18. The non-transitory computer readable storage medium as defined in claim 15, wherein the movement data includes data associated with a change in pressure of a hydraulic actuator that is operatively coupled to the folding portion.

19. The non-transitory computer readable storage medium as defined in claim 15, wherein the movement data of the folding portion is responsive to a triangular waveform.

16. A non-transitory computer readable storage medium comprising instructions, which when executed, cause a processor to at least:

determine a bias of a folding portion of an aerodynamic structure based on movement data of the folding portion to characterize a backlash associated with the folding portion; and

determine a calibration position of the folding portion based on the bias.