INTERLAMINAR FRACTURE TOUGHNESS OF MULTI-DIRECTIONAL LAMINATES  

多向层合板层间分层断裂韧性研究(英文)

作　　者：李勇[1] 李顺林[1] 陶杰[1] 

机构地区：[1]南京航空航天大学材料科学与技术学院

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2001年第2期176-181,共6页南京航空航天大学学报（英文版）

摘　　要：Based on the conventional compliance and area methods, a high precision method named the angle method is presented in this work. The interlaminar fracture toughness is determined by measurement of the load and the bending angle at the loading point without measurement of the crack length, and the improvement of the conventional compliance method is made, which is more precise and can be used to general DCB specimen with unequal flexural stiffness of the cantilevers. The interlaminar fracture toughness in 0/ θ(θ =0°,30°,60°,90°) interfaces of two epoxy composites, one being the carbon fibre reinforced brittle matrix T300/4211, the other the carbon fibre reinforced tough matrix T300/3261, is measured by both compliance and angle methods, and the relationship between fracture toughness and the ply angle θ is obtained. It is found that the interlaminar fracture toughness is correlated with the type of matrix and the ply angles near the crack front.在传统的柔度法和面积法的基础上 ,采用角度法对多向层合板层间分层断裂韧性进行了测试。该方法通过测量载荷与试验加载点处两子梁的夹角 ,不需要测量裂纹长度。同时对传统的柔度法进行了改进 ,改进后的柔度法可以用来测量两子梁刚度不等的 DCB试样。采用柔度法和角度法同时测试了碳纤维增强两种不同基体层合板 0 /θ(θ=0 ,30 ,6 0和 90°)层间分层断裂韧性 ,得出了分层断裂韧性随 θ的变化规律。这两种层合板分别为碳纤维增强脆性基体的 T30 0 / 4 2 1 1和碳纤维增强韧性基体的T30 0 / 32 6 1。结果发现 。

关 键 词：COMPOSITE LAMINATE DELAMINATION fracture toughness 

分 类 号：TB332[一般工业技术—材料科学与工程] V214.41.8[航空宇航科学与技术—航空宇航推进理论与工程]