The effects of thermal distribution on the composite panel flutter

To study the effects of temperature distribution on the critical flutter dynamic pressure and nonlinear limit cycle flutter amplitude of laminated composite panel, the assumptions of linear temperature distribution and nonlinear quadric temperature distribution were adopted in the finite element model of composite panel flutter with thermal effects. The thermal flutter equations of composite panel were solved in frequency domain and time domain for the critical flutter dynamic pressure and limit cycle flutter amplitude, respectively. The results show that the gradient effect of the linear temperature distribution decreases the critical flutter dynamic pressure while it increases the amplitude of limit cycle flutter, and the curvature effect of nonlinear quadric temperature distribution increases the critical flutter dynamic pressure. The even temperature distribution assumption will result in either a conservative flutter boundary or a risky flutter boundary. When the nonlinear effect of temperature distribution is significant, the effects of gradient effect and curvature effect of temperature distribution should be considered in panel thermal flutter solutions.