复合材料长桁末端拉伸数值分析与试验  

The Tensile Numerical Analysis and Experimental Research of Composite Stringerrunout

作　　者：杨鸽 苗志桃 张博平[2] Yang Ge;Miao Zhitao;Zhang Boping(AVIC Xi'an Aircraft Industry Group Company Ltd,Xi'an 710089,China;School of Aeronautics,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]中航西安飞机工业集团股份有限公司,陕西西安710089 [2]西北工业大学,航空学院,陕西西安710072

出　　处：《科学技术创新》2022年第4期49-52,共4页Scientific and Technological Innovation

摘　　要：为了预测复合材料长桁末端结构承受拉伸载荷时损伤起始与破坏过程,对复合材料长桁末端结构进行数值分析和试验研究。基于ABAQUS软件建立复合材料长桁末端渐进损伤分析模型,编写用户自定义场变量子程序(USDFLD)结合三维Hashin失效准则判断复合材料层合板的失效,采用二次名义应力准则作为长桁和壁板胶接界面的失效判据。结果表明:长桁末端结构承载能力数值分析结果和试验值较为接近,且分析的失效模式与试验结果一致,验证了考虑复合材料层合板失效及胶层脱粘模型的有效性。In order to predict the damage initiation and damage process of composite stiffened panel with stiffener runout under tensile load, numerical analysis and experimental research were carried out.Based on ABAQUS finite element software,theprogressive damage analysis model of composite stiffened panel with stiffener runout was established,the failure of composite laminates was judged by user-defined variable subroutine and 3 D Hashincriterion,the square stress failure criteria was used as the failure criteria ofadhesive interface.The result show that the finite analysis results of the bearing capability of the stiffener runout is consistent with the experimental values,the failure modes analyzed is consistent with the experimental results,verifying the reliability of the mode which takes failure of composite laminates and debonding of interface into consideration.

关 键 词：长桁末端 脱粘 渐近失效 失效模式 

分 类 号：TB33[一般工业技术—材料科学与工程]