Research On Suppression Of The Panel Flutter Based On Non-probabilistic Reliability Theory

Aircraft during the process of with hypersonic fight, often occur accidents frequentlybecause of panel flutter problem. In this paper, the study of the hypersonic vehicle compositepanel is present. Based on the theory of non-probabilistic reliability, the effect of the vibrationsuppression of the panel considering structure uncertain parameters under the H∞controlling system and the robust reliability are analyzed in details.First of all, the controlling system is furnished with piezoelectric patches as active controlactuator and the first order piston theory as aerodynamic force. Using the Hamilton theory，the unit vibration function of the panel is established. Then the dynamic function of the finiteelement vibration considering structure uncertain parameters under active control are given byunit assembling.In addition, by taking advantage of the kinematics equation,the state space equationswith structure uncertain parameters of the panel are built. And the sensitivity of thetransformation matrix are derived by using the balanced order reduction method and solvingthe controllable sensitivity with observability and eigen-pairs given by orthogonaltransforming the symmetric matrix.Then the reduced uncertain system are obtained by theusing the Taylor’s expansion.Based on the H∞state-feedback control theory, the H∞state-feedback controller canexist if and only if the linear matrix inequality holds. Then the performance function can beestablished for measuring the robust controller performance reliability. And thenon-probabilistic reliability indexes are given by making using of the theory ofnon-probabilistic reliability. Taking advantage of the method of LMI and robust reliability, thestate feedback controller considering the uncertain parameters is derived. The gains of thecontroller are discussed under different reliabilities.Finally, the numerical examples calculations of the panel are given by the Matlab. Forone thing, the validity of the motion equations of the composite panel under active control are verified. For another, the feedback controller of the composite panel satisfying the robust andconsidering the uncertain parameters are derived. Then the effect of controller is verified atlast.