| 摘要 |
A method for assessing the dynamic stiffness of a flight control actuator comprising the steps of (1) providing a control surface actuator system including an actuator having a portion thereof coupled to an aircraft control surface; (2) applying a command signal to the actuator control system, causing the production of a pressure differential across the actuator in response to the command signal based on the ability of the actuator to react to an inertial load generated by the attempted acceleration of the control surface; and (3) processing a pressure signal representative of the pressure differential produced across the actuator.
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