含界面脱粘三维五向编织复合材料单向拉伸损伤失效机理研究  

Damage and Failure Mechanism Analysis of 3D Five-Directional Braided Composites with Interface Debonding under Unidirectional Tension

作　　者：张超[1] 许希武[1] 郭树祥[1] 

机构地区：[1]南京航空航天大学结构与强度研究所飞行器结构力学与控制教育部重点实验室,南京210016

出　　处：《航空材料学报》2011年第6期73-80,共8页Journal of Aeronautical Materials

基　　金：国家自然科学基金(10672075)

摘　　要：建立了含界面脱粘的三维五向编织复合材料单向拉伸损伤分析有限元模型。将Tsai-Wu强度准则用于纤维束损伤判断并确定材料失效模式,结合Murakami损伤张量表征材料各向异性损伤,根据失效模式进行材料性能退化;界面相和基体分别采用Quads准则和Mises准则作为失效判据,引入刚度折减;建立了五向编织复合材料的损伤预测模型。模拟了典型编织角材料的细观损伤起始、扩展和最终失效过程,分析了材料的细观损伤失效机理,并基于所得应力应变曲线预测了材料的拉伸强度。数值结果与试验结果基本吻合,说明了损伤预测模型的合理有效性。A nonlinear finite element model with interface phase was presented to simulate the damage and failure of 3D five-directional braided composites under unidirectional tension.Tsai-Wu and Mises criterions were considered for initial damage prediction of yarns and matrix.Quads failure criteria was adopted to identify the onset of debonding of the interface.An anisotropic damage model was used to analyze the damage evolution of yarns those damage modes were characterized by Murakami＇s damage tensor.In addition,a isotropic damage model was used to matrix and interface.The whole process of damage initiation,propagation and catastrophic failure of five-directional braided composites with typical braided angle were simulated in detail.The damage mechanisms were revealed in the simulation process and the strength of the braided composites was predicted from the calculated stress-strain curve.The numerical results show good consistent with experiment results,which verifies that the proposed simulation method is very useful for the evaluation of damage mechanisms of 3D five-directional braided composites.

关 键 词：三维五向 编织复合材料 界面脱粘 失效机理 强度预测 

分 类 号：TB332[一般工业技术—材料科学与工程]