压电复合材料壁板颤振的控制

苑凯华; 邱志平

压电复合材料壁板颤振的控制

北京航空航天大学航空科学与工程学院, 北京 100191

基金项目: 航天科技创新基金资助项目; 航空科学基金资助项目(2007ZA51003); 高等学校学科创新引智计划资助项目(B07009)

详细信息

作者简介:
苑凯华(1983-), 女, 河北保定人, 博士生, king101010@sohu.com.

中图分类号: O 326
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- 文章访问数: 3402
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- 被引次数: 0
出版历程
- 收稿日期: 2008-11-12
- 网络出版日期: 2009-12-31

Flutter control of composite panels with embedded piezoelectric materials

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对考虑热效应的壁板颤振问题,利用von Karman大变形应变-位移关系、气动力活塞理论和准定常热应力理论建立了埋入压电材料的复合材料板颤振的气动弹性力学模型,使用Bogner-Fox-Schmit单元推导出壁板颤振的非线性有限元方程.将该动力学方程转换到状态空间模型,给出了基于这个非线性模型的最优控制.应用Runge-Kutta方法在时域内对一个四边简支的含压电材料的复合材料壁板颤振的控制进行了仿真,数值结果证明了该方法的有效性.
- 壁板颤振 /
- 活塞理论 /
- 热应力理论 /
- 有限元 /
- 压电材料
Abstract: The panel flutter phenomenon with thermal effect was researched. By virtue of von Karman-s large deflection plate theory, piston theory aerodynamics and the quasi-steady thermal stress theory, the aeroelastic model of composite panel with embedded piezoelectric materials was established. In nonlinear finite element equation the Bogner-Fox-Schmit element was adopted. The dynamic equations of motion were transformed into a state space model in order to design controller. An optimal controller based on the nonlinear model was presented. The flutter suppression results in the time domain using the Runge-Kutta method for a simply supported piezolaminated composite panel subjected to uniform thermal loading was realized. The effectiveness of the present control method was illustrated by simulation solution.
- panel flutter /
- piston theory /
- thermal stress theory /
- finite element method /
- piezoelectric materials

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参考文献(1)

[1] Dowell E H.Aeroelasticity of plates and shells[M].Netherlands:Noordhoff International Publishing,1975:1-9 [2] Gray C E,Mei C,Shore C P.Finite element method for large-amplitude two-dimensional panel flutter at hypersonic speeds[J].AIAA Journal,1991,29(2):290-298 [3] Xue D Y,Mei C.Finite element nonlinear panel flutter with arbitrary temperatures in supersonic flow[J].AIAA Journal,1993,31(1):154-162 [4] Li Qinqin,Mei C,Huang J K.Suppression of thermal postbuckling and nonlinear panel flutter motions using piezoelectric actuators [J].AIAA Journal,2007,45(8):1861-1873 [5] Koconis D B,Kollar L P,Springer G S.Shape control of composite plates and shells with embedded actuators Ⅰ:voltages specified[J].Journal of Composite Materials,1994,28(5):415-458 [6] 方有亮,武哲.配置压电自感作动器复合层板的振动主动控制[J].航空学报,2000,21(3):247-250 Fang Youliang,Wu Zhe.Active vibration control of composite plate with self-sensing piezoelectric actuators[J].Acta Aeronautica et Astronautica Sinica,2000,21(3):247-250(in Chinese) [7] 咸奎成,黄海.自适应压电桁架形状控制中作动器优化配置[J].北京航空航天大学学报,2007,33(5):527-530 Xian Kuicheng,Huang Hai.Optimal actuator placements for shape control of adaptive piezoelectric truss[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(5):527-530(in Chinese) [8] 胡举喜,邱志平.压电层合板振动的鲁棒控制[J].北京航空航天大学学报,2008,34(8):873-876 Hu Juxi,Qiu Zhiping.Using the robust control method to control the vibration piezoelectric laminated plates[J].Journal of Beijing University of Aeronautics and Astronautics,2008,34(8):873-876(in Chinese) [9] 吴大方,刘安成,麦汉超,等.压电智能柔性梁振动主动控制研究[J].北京航空航天大学学报,2004,30(2):160-163 Wu Dafang,Liu Ancheng,Mai Hanchao,et al.Study on active vibration control of piezoelectric intelligent flexible beam[J].Journal of Beijing University of Aeronautics and Astronautics,2004,30(2):160-163(in Chinese) [10] Cheng Guangfeng.Finite element modal formulation for panel flutter at hypersonic speeds and elevated temperatures .Virginia:Department of Engineering Mechanics,Old Dominion University,2002 [11] Zhou R C,Xue D Y,Mei C.A finite element time domain-modal formulation for nonlinear flutter of composite panels[J].AIAA Journal,1994,32(10):2044-2052 [12] Junkins J L,Kim Y.Introduction to dynamics and control of flexible structures[M].Washington D C:AIAA,1993:287

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