Semi-active flutter suppression for wing aileron with framework system

A typical wing aileron system with a rudder driver framework is investigated. The magenetorheological (MR) damper is fixed on the framework instead of the aileron rotation axis. A set of four-degrees-of-freedom aeroelastic differential equations is developed and the on-off control algorithm is used to attenuate the vibration of the aileron. The numerical results show that the critical flutter speed is insensitive to the hysteresis of the MR damper. The higher apply voltage and the shorter control delay time can greatly increase the critical flutter speed. This configuration of the MR damper under the on-off control strategy can increase the critical flutter speed by 17% at least.