# US 10,370,084 B2 · Methods and apparatus to adjust folding wing tips

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- Number: US 10,370,084 B2
- Document ID: US10370084B2
- Status: Granted
- Kind: B2
- Application number: 15/656,840
- Filed: 2017-07-21
- Published: 2019-01-24
- Granted: 2019-08-06
- Earliest claimed: 2017-07-21
- Assignees: The Boeing Company
- Applicants: The Boeing Company
- Inventors: Paul Jay Cline; Arnold F. Agdamag
- Web page: https://patentgrep.com/patent/US10370084B2

## CPC

- B64C 3/56: Folding or collapsing to reduce overall dimensions of aircraft
- Y02T 50/10: Drag reduction
- B64C: AEROPLANES; HELICOPTERS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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

### Claim 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.

### Claim 2 (depends on 1)

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

### Claim 3 (depends on 1)

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

### Claim 4 (depends on 1)

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.

### Claim 5 (depends on 4)

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.

### Claim 6 (depends on 1)

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

### Claim 7 (depends on 1)

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

### Claim 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.

### Claim 9 (depends on 8)

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

### Claim 10 (depends on 8)

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

### Claim 11 (depends on 8)

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.

### Claim 12 (depends on 8)

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

### Claim 13 (depends on 8)

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

### Claim 14 (depends on 13)

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

### Claim 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.

### Claim 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.

### Claim 17 (depends on 15)

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.

### Claim 18 (depends on 15)

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.

### Claim 19 (depends on 15)

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.