Prediction and active suppression of flutter in composite panel based on eigenvector orientation method

In this paper, the critical points of flutter of a composite panel predicted using a finite element model are studied using an eigenvector orientation method. Taking a supersonic simply supported panel and clamped panel models as examples, the accuracy of the eigenvector orientation method for predicting the critical points of flutter is verified, and the misjudgments of “channeling” (modal crossover) and other phenomena by traditional judgment methods are avoided. The piezoelectric actuators are combined with the upper and lower surfaces of the simply supported panel (clamped panel), and the aerodynamic parameters of each finite element are changed by activating the piezoelectric actuators. Based on linear quadratic adjustment theory, an optimal control method for the active flutter suppression is designed. The influence of the activation position of the different piezoelectric actuators on the critical points of flutter is studied to increase the flutter speed to an ideal range. The results show that the control torque generated by the piezoelectric actuators can offset the occurrence of flutter and provide a lead time for possible flutter control.