智能复合材料机翼颤振分析  

Flutter analysis of an intelligent composite wing

作　　者：高为浪[1] 张景文[2] 韩景龙[3] 

机构地区：[1]安徽工业大学机械工程学院,安徽马鞍山243002 [2]兰州理工大学流体动力与控制学院,甘肃兰州730050 [3]南京航空航天大学航空宇航学院,江苏南京210009

出　　处：《兰州理工大学学报》2007年第4期35-39,共5页Journal of Lanzhou University of Technology

摘　　要：利用哈密尔顿原理和半李兹分析法建立复合材料悬臂板的运动方程,结合边界条件得到其弯扭耦合模态的半解析解.建立具有NACA0012翼型且贴有压电作动器和压电传感器的复合材料机翼的运动方程,利用西奥道生理论,形成智能复合材料机翼气动弹性问题的描述,利用U-g法预测复合材料机翼的颤振速度.通过数值仿真,针对智能复合材料机翼闭环系统中的不同反馈增益系数,计算模态振型和颤振速度.结果表明,不同的反馈增益系数,对模态振型和颤振速度有一定的影响.Dynamic equations were established first for the composite cantilever plates by means of Hamilton principle and the semi-Ritz analytical method and the semi-analytical expressions for the coupled modes of bending and torsion of the composite cantilever plates were derived according to its boundary conditions. Then the dynamic equations were established for the intelligent composite wing with NACA0012 airfoil, piezoelectric actuator, and piezoelectric sensor. The Theodorsen theory was employed to model aerodynamics and the flutter speed of the intelligent-composite wing was predicted by utilizing U-g method. By means of numeric simulation, the mode patterns and the flutter speed were evaluated for several gains used in the displacement negative feedback closed-loop system of the intelligent composite wing. The results indicated that the mode patterns and flutter speed were definitely influenced by the different feedback gains.

关 键 词：智能复合材料机翼 耦合模态 颤振 西奥道生理论 

分 类 号：V214.3[航空宇航科学与技术—航空宇航推进理论与工程] TH113.1[机械工程—机械设计及理论]