| 摘要 |
An actuator system (10, 100, 200) for use in an aircraft control or operating system, comprising a controller (12) operable in response to an input for generating a control signal, and an electrical actuator (20) responsive to the control signal for operating an aircraft flight control surface or other aircraft apparatus. A tab (24; 124) for aerodynamically assisting the electrical actuator is also provided in order to reduce the load on the electrical actuator in use.
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