碳纤维层合板弹体冲击仿真方法研究  

Simulation of Ballistic Impact on Carbon Fiber Laminate Panels

作　　者：陆晓[1] 宣海军[1] 廖连芳[2] 

机构地区：[1]浙江大学高速旋转机械实验室,杭州310027 [2]沈阳航空发动机设计研究所,沈阳110015

出　　处：《材料工程》2009年第S2期25-28,共4页Journal of Materials Engineering

基　　金：航空推进技术验证计划项目(APTD-1104-03)

摘　　要：为了研究碳纤维增强复合材料层合机匣对高速撞击碎片的包容能力,通过LS-DYNA对圆柱弹体撞击BMS8-212层合增强复合材料进行动态仿真计算。有限单元计算模型中,层板材料采用连续损伤材料本构模型,层间采用固连失效接触模式。通过与试验结果的比较,验证了数值仿真方法的可靠性。发现,纤维增强复合材料层合板在弹体的横向高速撞击下主要的失效形式为纤维剪切、纤维和基体挤压、分层破坏、拉伸失效。In order to study the contain capability of debris high speed impact on carbon fiber-reinforced composite laminate case,simulations of cylindrical projectile impact on BMS8-212 laminate composite panels have been carried using LS-DYNA software.Continuum damage constitutive model for plies and automatic tiebreak mode for laminate failures are introduced in the finite element model.Through comparison with the experimental results,the reliability of the numerical simulation methods is verified.It is found that the failure patterns of fiber-reinforced composted laminated plate impacted with high speed projectile are fiber shear failure,fiber and matrix crush failure,delamination and fiber tensile failure.

关 键 词：纤维增强复合材料层合板 冲击破坏 航空发动机 复合材料机匣 叶片包容 

分 类 号：TB302.3[一般工业技术—材料科学与工程]