Suppression of thermal postbuckling and nonlinear panel flutter motions of variable stiffness composite laminates using piezoelectric actuators  

变刚度复合材料层合板的热后屈曲和颤振的主动控制

作　　者：TAO Ji-xiao YI Sheng-hui DENG Ya-jie HE Xiao-qiao 陶基笑;易圣辉;邓亚洁;何小桥(Department of Mechanics and Aerospace Engineering,Southern University of Science and Technology,Shenzhen 518055,China;Centre for Advanced Structural Materials,City University of Hong Kong Shenzhen Research Institute,Shenzhen 518057,China;School of Aerospace Engineering and Applied Mechanics,Tongji University,Shanghai 200092,China;Department of Architecture and Civil Engineering,City University of Hong Kong,Tat Chee Avenue,Kowloon,Hong Kong,China)

机构地区：[1]Department of Mechanics and Aerospace Engineering,Southern University of Science and Technology,Shenzhen 518055,China [2]Centre for Advanced Structural Materials,City University of Hong Kong Shenzhen Research Institute,Shenzhen 518057,China [3]School of Aerospace Engineering and Applied Mechanics,Tongji University,Shanghai 200092,China [4]Department of Architecture and Civil Engineering,City University of Hong Kong,Tat Chee Avenue,Kowloon,Hong Kong,China

出　　处：《Journal of Central South University》2021年第12期3757-3777,共21页中南大学学报（英文版）

基　　金：Project(JCYJ20190808175801656)supported by the Science and Technology Innovation Commission of Shenzhen,China;Project(2021M691427)supported by Postdoctoral Science Foundation of China;Project(9680086)supported by the City University of Hong Kong,China。

摘　　要：Variable stiffness composite laminates(VSCLs)are promising in aerospace engineering due to their designable material properties through changing fiber angles and stacking sequences.Aiming to control the thermal postbuckling and nonlinear panel flutter motions of VSCLs,a full-order numerical model is developed based on the linear quadratic regulator(LQR)algorithm in control theory,the classical laminate plate theory(CLPT)considering von Kármán geometrical nonlinearity,and the first-order Piston theory.The critical buckling temperature and the critical aerodynamic pressure of VSCLs are parametrically investigated.The location and shape of piezoelectric actuators for optimal control of the dynamic responses of VSCLs are determined through comparing the norms of feedback control gain(NFCG).Numerical simulations show that the temperature field has a great effect on aeroelastic tailoring of VSCLs;the curvilinear fiber path of VSCLs can significantly affect the optimal location and shape of piezoelectric actuator for flutter suppression;the unstable panel flutter and the thermal postbuckling deflection can be suppressed effectively through optimal design of piezoelectric patches.变刚度复合材料层合板可以通过改变纤维角度和铺层顺序来设计其材料性能,因此在航空航天领域具有广阔的应用前景。本文基于控制理论中的LQR算法、在经典的层合板理论中考虑几何非线性并结合一阶活塞理论建立了用于分析变刚度板的热后屈曲和气弹性颤振的有限元模型。通过参数分析,预测了变刚度复合材料板的屈曲温度和临界气动压力。通过比较反馈控制增益(NFCG)的值,确定了控制变刚度板后屈曲变形和气弹性颤振的压电控制器的最优位置和形状。数值模拟结果表明:温度场对变刚度复合材料板的气动弹性设计有重要的影响;纤维路径的变化对压电控制器的最优位置和形状有显著影响;通过压电片的优化设计,板的颤振和热后屈曲变形可以得到有效的抑制。

关 键 词：active control finite element method linear quadratic regulator algorithm nonlinear flutter thermal postbuckling variable stiffness composite laminates 

分 类 号：TB33[一般工业技术—材料科学与工程]