Dynamics modeling of piezoelectric control for the aircraft wings in aerodynamic thermal environment

In this paper, the aircraft wings are simplified as the cantilever beam structure. Piezoelectric actuator is used to eliminate the effects in the thermal environment. Mathematical modeling of cantilever beam in the temperature field are built. Simulation of the accessional control by piezoelectric film model show the feasibility of the control method preliminarily. And our purpose is enhance the performance of the structures on the base of general materials by using smart material and effective control methods in the future.