复合材料壁板热颤振的有限元分析

Flutter Analysis of Composite Panels with Thermal Effects

壁板颤振是发生在高速飞行器上的一种典型的超音速气动弹性现象。在超音速飞行器的设计中,由于气动加热效应相当剧烈,考虑热效应的壁板颤振问题成为一个不可忽视的气动弹性问题。文中采用vonKarman大变形应变-位移关系、气动力活塞理论以及准定常热应力理论建立了考虑热效应的复合材料壁板颤振的气动弹性力学模型。使用计及壁板横向剪切效应的三结点三角形Mindlin板单元(MIN3单元)推导出考虑热效应的颤振有限元方程,并给出了在频域和时域求解其颤振方程的方法。分别对一个矩形复合材料壁板和梯形复合材料壁板,计算出壁板的颤振边界并分析了温度对壁板颤振边界的影响规律。

Panel flutter is a typical supersonic aeroelastic phenomenon taking place in high speed aircraft. Because of the drastic aerodynamic heating effect, panel flutter analysis considering thermal effects becomes an emerging problem in the design process of supersonic aircraft. The aeroelastic model of composite panel with thermal effects is established using von Karman large deformation strain-displacement relationship, piston theory of aerodynamics and quasi-steady theory of thermal stress. In panel flutter equations three-node triangular Mindlin plate element is adopted to consider the transverse shear effect of composite panels. The solving approaches for panel flutter equations in time domain and frequency domain are also presented. The flutter boundaries are calculated for a rectangular composite panel and a trapezoidal composite panel respectively, and the effects of temperature on flutter boundaries are discussed.