基于三角剪切变形理论的对称层合板振动分析  

Vibration analysis of symmetric laminated composite plates by trigonometric shear deformation theory

作　　者：杨明绥[1] 李大鹏[1] 洪志亮[2] 武卉[1] 路卫华[3] 梅繁[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015 [2]中航工业沈阳黎明航空发动机(集团)有限责任公司,沈阳110043 [3]中航沈飞民用飞机有限责任公司,沈阳110034

出　　处：《沈阳航空航天大学学报》2012年第3期5-9,共5页Journal of Shenyang Aerospace University

摘　　要：根据三角剪切变形层合梁理论,推导出对称复合材料层合板的运动微分方程,利用逆复合二次径向基函数无网格配点法对运动微分方程进行离散,预测了对称复合材料层合板的自由振动特性。将不同材料参数、几何尺寸的层合板固有频率计算结果与相关文献中的结果进行对比,结果表明:用逆复合二次径向基函数离散的三角剪切变形理论在对称复合材料层合板自由振动分析方面具有一定的精度。Based on the trigonometric shear deformation theory for laminated beams, the motion differential equation of symmetric laminated composite plates is deduced. The motion differential equation discretized by a meshless collocation method based on the inverse multiquadric radial basis function is used to predict the free vibration behavior of symmetric laminated composite plates. Natural frequencies are computed for various material parameters, geometry parameters of laminated plates, and compared with some available published results. Through numerical experiments, the high numerical accuracy of trigonometric shear de- formation theory discretized by the inverse multiquadric radial basis function for free vibration analysis of symmetric laminated composite plates are demonstrated.

关 键 词：三角剪切变形理论 复合材料层合板 振动 逆复合二次径向基函数 

分 类 号：V214.33[航空宇航科学与技术—航空宇航推进理论与工程]