Methods and apparatus to adjust folding wing tips
AssigneeThe Boeing Company
InventorsPaul Jay Cline, Arnold F. Agdamag
Life of this patent
Estimating the term…
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.
Claims19
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.
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.
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.
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.
Dependencies are inferred from the claim text.