Patent ID: 11884380
Assignee: THE BOEING COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B  Y | IPC B

Claim 11:
12. The method of claim 8, wherein the wing is a first wing; wherein the flight control surface is a first flight control surface; wherein the flight control surface actuation system is a first flight control surface actuation system; wherein the skew detection system is a first skew detection system; wherein the hybrid sensing actuator is a first hybrid sensing actuator; wherein the actuator output is a first actuator output; wherein the actuator output position sensor is a first actuator output position sensor; wherein the actuator output position signal is a first actuator output position signal that indicates a position of the first actuator output; wherein the vehicle further comprises a second wing with a second flight control surface and a second flight control surface actuation system for operating the second flight control surface; wherein the second flight control surface actuation system includes a second skew detection system configured to detect a skew condition in the second flight control surface; wherein the second skew detection system includes a second hybrid sensing actuator with a second actuator output and a second actuator output position sensor configured to generate a second actuator output position signal that indicates a position of the second actuator output; and wherein the generating the skew condition signal includes comparing the first actuator output position signal and the second actuator output position signal.