T300/6511复合材料[(±45)]_(5)平纹织物层合板拉-拉疲劳断裂行为研究  

Study on tension-tension fatigue fracture behavior of T300/6511 composites[(±45)]_(5)plain weave laminates

作　　者：汪莹 李敏 李桃山 杨琴 WANG Ying;LI Min;LI Taoshan;YANG Qin(Airforce Aviation Repair Institute of Technology,Changsha 410124,China;Changsha 5712 Aircraft Industry Co.Ltd.,Changsha 410113,China)

机构地区：[1]空军航空维修技术学院,湖南长沙410124 [2]长沙五七一二飞机工业有限责任公司,湖南长沙410113

出　　处：《兵器材料科学与工程》2023年第6期36-41,共6页Ordnance Material Science and Engineering

基　　金：湖南省自然科学基金科教联合基金项目(2020JJ7078);长沙航空职业技术学院院级课题一般项目(YC2301)。

摘　　要：为研究飞机结构用T300/6511碳纤维复合材料疲劳性能,开展了该材料[(±45)]_(5)平纹织物层合板的准静态拉伸试验和4种应力水平下的拉-拉疲劳试验,通过超景深三维显微镜、超声波C扫和扫描电子显微镜(SEM),观察和分析了试样的断口形貌和内部损伤,研究了该层合板疲劳损伤积累和断裂过程。结果表明:T300/6511碳纤维复合材料[(±45)]_(5)平纹织物层合板的平均剪切强度为106.5 MPa,50%的应力水平下循环次数近5×10^(5),拟合的疲劳等寿命公式为u=0.058+0.196×lg N;层合板的疲劳裂纹首先萌生于表层及外轮廓边缘,随后层内基体裂纹跨层发展,最后,层间大面积分离,伴随着大量纤维断裂,试样表现为多种损伤形式的失效。In order to study the fatigue performance of T300/6511 carbon fiber composite used in aircraft structures,quasi-static tensile tests and tensile fatigue tests were conducted on the[(±45)]_(5)plain woven fabric laminates,the fracture morphology and internal damage of the laminates were observed and analyzed through ultra-depth 3D microscope,ultrasonic C-scan and SEM,and the accumulation and fracture process of fatigue damage in the laminates were studied.The results show that T300/6511 carbon fiber composite[(±45)]_(5)plain woven laminates have an average shear strength of 106.5 MPa,and the number of fatigue cycles reaches nearly 5×10^(5)at 50%stress level.A fitted fatigue iso-life formula is u=0.058+0.196×lgN.The fatigue cracks of the laminates firstly initiate with the edge of the surface layer and the outer contour,then the cracks develop inward across the layers,and finally a large number of long cracks appear between the layers accompanied by fiber fracture,indicating that the failure of the laminates is caused by various damage modes.

关 键 词：织物层合板 拉-拉疲劳 疲劳寿命 疲劳断裂 

分 类 号：TQ327.3[化学工程—合成树脂塑料工业]