单向带复合材料0°拉伸疲劳试样构型对比分析及失效机理研究  

Comparative analysis and failure mechanism study of 0°tensile fatigue specimen configuration of unidirectionalstrip composite materials

作　　者：黄光启 宋贵宾 张强[1] HUANG Guangqi;SONG Guibin;ZHANG Qiang(National Key Laboratory of Strength and Structural Integrity,China Aircraft Strength Research Institute,710065 Xi'an,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,西安710065

出　　处：《应用力学学报》2025年第1期64-70,共7页Chinese Journal of Applied Mechanics

摘　　要：对常用的2种单向带复合材料0°拉伸疲劳试样构型开展了试验与仿真分析对比研究,通过采用非接触测量手段获取了2种构型试样在拉伸载荷下的应变分布,发现“双哑铃型”试样边缘效应显著,应力集中更加严重;同时通过仿真分析方法获取了2种构型试样在拉伸载荷下的应力云图,同样表明“双哑铃型”应力集中严重;通过电子显微镜观察试样边缘发现机械加工将导致试样表面损伤,“双哑铃型”试样在机械加工过程中将对纤维造成更多损伤,不利于承载;试验与分析结果表明“直条型”试样较“双哑铃型”试样更适合开展碳纤维增强复合材料0°拉-拉疲劳门槛值试验。This article conducted experimental and simulation analysis and comparative research on two commonly used unidirectional composite material 0°tensile-fatigue specimen configurations.By using non-contact measurement methods,the strain distribution of the two configuration specimens under tensile load was obtained.It was found that the“double dumbbell shaped”specimen had significant edge effects and more severe stress concentration.At the same time,stress cloud maps of two types of specimens under tensile load were obtained through simulation analysis methods,which also showed severe stress concentration in the“double dumbbell shaped”specimen.By observing the edges of the sample under an electron microscope,it was found that mechanical processing would cause surface damage to the sample.The“double dumbbell shaped”sample would cause more damage to the fibers during mechanical processing,which is not conducive to load-bearing.The experimental and analytical results indicate that the“straight strip”specimen is more suitable for conducting 0°tensile-fatigue threshold tests on carbon fiber composite materials than the“double dumbbell”specimen.

关 键 词：碳纤维复合材料 疲劳门槛值 试样构型 失效机理 试验方法 

分 类 号：V216.1[航空宇航科学与技术—航空宇航推进理论与工程]