Simulation analysis of piezoelectric cantilever beam control in thermal enviroment

Spacecraft´s wing surface just like wing, solar panel, satellite antenna and so on can have local high temperature because of high-speed friction with the air of atmosphere and solar radiation in outer space, while upper atmosphere or outer space that light can not strikes have low temperature. Because of these, the wing surface´s local stiffness, surface shape and vibration characteristic of mode shape can be changed, and then the spacecraft´s normal work can be damaged. In this paper, Spacecraft´s wing can be simplified to cantilever beam. And then simulate the simplified model in thermal environment by ANSYS, the reason why the stiffness changes under the temperature is discussed. And then, put forward approaches which use piezoelectricity material control to change the stiffness influenced by different temperature gradients.