首页 | 本学科首页   官方微博 | 高级检索  
     检索      

考虑剪切效应的复合材料层合板阻尼特性研究
引用本文:王文博,漆文凯,沈承.考虑剪切效应的复合材料层合板阻尼特性研究[J].航空发动机,2018,44(3):60-64.
作者姓名:王文博  漆文凯  沈承
作者单位:南京航空航天大学江苏省航空动力系统重点实验室
摘    要:为了对复合材料结构设计模型进行优化,基于Hencky假设,考虑剪切应力的影响,建立了复合材料层合板的有限元分析模型,在微观力学角度上改进3相桥联模型,预测能量损耗因子,获得目标复合材料层合板的固有频率、振型以及比阻尼容量等振动相关参数。以碳纤维材料层合板为例,将计算结果与现有文献结果进行对比,验证了改进模型的正确性。矩形层合板具体分析结果表明:复合材料层合板在一端固支下,无论是长度还是宽度的变化,对第1阶固有频率的影响都很微弱;第4、5阶固有频率表现出趋于同频现象,振型也会产生类似变化趋势;在长度和宽度变化下,第6阶模态结果则表现出相反的对数变化轨迹。

关 键 词:Hencky  板/  壳理论  复合材料层合板  有限元  比阻尼容量

Research on Damping Characteristic of Composite Laminated Plates Considering Shear Effect
Authors:WANG Wen-bo  QI Wen-kai  SHEN Cheng
Institution:Jiangsu Province Key Laboratory of Aerospace Power System,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
Abstract:To optimize the composite structure design model, based on the Hencky hypothesis,the finite element analysis model of the composite laminated plates was established considering the influence of shear stress. The three-phase bridge model was improved from the angle of micromechanics,the energy loss factor was predicted,the natural frequency of the composite laminated plates,vibration parameters such as vibration mode and specific damping capacity were obtained. Taking the carbon fiber laminated plates for example,the calculation results were compared with the existing literatures,and the correctness of the improved model was verified. The analysis results of rectangular laminated plates show that,both length and width changes of the composite laminated plates,clamped on one side, has a slight influence on the natural frequency of the first order; the fourth and fifth orders tend to common frequency, and the vibration mode has the same variation tendency; while results of the sixth order mode show contrary logarithm varying trajectory as the length and width change.
Keywords:Hencky plate / shell theory  composite laminated plates  finite element  specific damping capacity
本文献已被 CNKI 等数据库收录!
点击此处可从《航空发动机》浏览原始摘要信息
点击此处可从《航空发动机》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号