平纹编织复合材料层合板静态压缩与压-压疲劳性能  

Static compression and compression-compression fatigue properties of plain woven composite laminates

作　　者：张铁纯[1] 杨晨晨 王轩[1] 周春苹 ZHANG Tiechun;YANG Chenchen;WANG Xuan;ZHOU Chunping(Aeronautical Engineering Institute,Civil Aviation University of China,Tianjin 300300,China;Aviation Key Lab of Science and Technology on High Performance Electromagnetic Windows,AVIC Research Institute for Special Structure of Aeronautical Composite,Jinan 250023,China)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]航空工业济南特种结构研究所高性能电磁窗航空科技重点实验室,济南250023

出　　处：《航空材料学报》2022年第2期64-72,共9页Journal of Aeronautical Materials

基　　金：天津市科技计划项目(20YDTPJC00380);中央高校基本科研业务费中国民航大学专项(3122019099)。

摘　　要：采用电液伺服疲劳试验机开展玻璃纤维平纹编织复合材料层合板的静态压缩和压-压疲劳性能实验。应力比为R=10,拟合出S-N曲线,基于疲劳实验过程中的刚度退化、能量耗散、循环蠕变与循环软化来表征疲劳损伤演化,结合扫描电子显微镜对断口形貌进行观察。结果表明:试件的条件疲劳极限为静态压缩强度的66.3%;通过双加权最小二乘法拟合的S-N曲线具有较高可信度;随着循环次数的增加,试件刚度逐渐下降,各峰值载荷下的能量耗散逐渐增加;在循环加载初期,试件表现出强烈循环蠕变现象,高峰值载荷作用下的试件表现出强烈循环软化行为;试件经过循环加载抵抗变形能力得到增强;断口观察到了基体开裂、纤维/基体界面脱粘、纤维断裂和分层四种失效模式;与疲劳断口相比,静态压缩断口表现出较大的分层损伤。The static compression and compression-compression fatigue tests of glass fiber plain woven composite laminates were carried out on an electro-hydraulic servo fatigue testing machine. The stress ratio was R=10, and the S-N curve was fitted. The fatigue damage evolution was characterized by stiffness degradation, energy dissipation, cyclic creep and cyclic softening during fatigue tests. The fracture morphology was observed by scanning electron microscope. The results show that the conditioned fatigue limit is66.3% of the static compressive strength. The S-N curve fitted by the double-weighted least square method has high reliability. With the increase of the number of cycles, the stiffness of the test piece decreases gradually, and the energy dissipation under each peak load increases gradually. At the initial stage of cyclic loading, the test pieces exhibit strong cyclic creep phenomenon, and the test pieces under the peak load exhibit strong cyclic softening behavior. The resistance to deformation of the test piece is enhanced after cyclic loading. Four failure modes including matrix cracking, fiber/matrix interface debonding, fiber fracture and delamination are observed. Compared with fatigue fracture, the static compression fracture shows larger delamination damage.

关 键 词：复合材料 疲劳 S-N曲线 刚度退化 能量耗散 断口形貌 

分 类 号：TB332[一般工业技术—材料科学与工程]