The flutter suppression of composite panel and the actuator placement optimization

This paper present the characteristics of a cantilevered piezoelectric composite wing model, idealized as a composite flat plate. Based on the Hamilton principle, the dynamic equation of the piezoelectric composite plane is deduced. The aerodynamic force acting on the surface of the composite plane is computed in frequency domain using the doublet lattices method, fitted and transformed to time domain using the minimum state method. The state space equation of composite plane including controlling is established. The optimal placement of piezoelectric active and sensor are selected using the genetic algorithm under the objection including both minimization of the states and the control effort. The result present that the position of the piezoelectric have great influence on the effect of control. Better control effect could be got with optimal piezoelectric placement.