According to airworthiness regulations,the design requirements and methods of aircraft control surface vibration werestudied.The calculation methods of actuator dynamic stiffness and free clearance limit cycle oscillation of aircraft control surface were discussed.Aiming at the aileron vibration problem found in flight test of a large turboprop aircraft,the causes of the abnormal aileron vibration were expounded,and the finite element model of structural dynamics was established to carry out the frequency response analysis of aileron control stiffness and damping with variable parameters and study the vibration char-acteristics of aileron.Then,a temporary method to improve the damping of aileron booster piston by punching holes and a method to optimize aileron structure and system according to the requirements of control surface vibration design and free clearance control were proposed.After the improved design of aileron,the analysis of test flight data showed that the vibration response amplitude of aileron decreased obviously and the vibration convergence was good,guaranteeing the continued devel-opment of the flight test.
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