摘要
对复合材料层合板进行了横向静态压痕试验,得到了载荷-位移曲线。依据曲线上的位移值,采用九节点壳单元、三维Tsai-W u失效判和损伤层刚度折减方法,对准静态压痕损伤进行了计算,并与超声C扫描压痕损伤检测图像做了比较。结果表明,损伤仿真与实际损伤检测图一致性好。
Tests are performed, measuring load - deformation curves in a fiber reinforced composite laminations subjected to transverse static load. Using 9-nodes shell element and 3-D Tsai-Wu failure criterion and the method of local stiffness depression for damage lamina, the indentation damage of composite laminations is calculated in according to the displacement value of load-deformation curve obtained, and the actual damage shape and size of the laminate are obtained by means of Ultrapact II C - scan device. The results of damage simulation are coincided with the test ones after comparison.
出处
《航空计算技术》
2006年第6期21-23,共3页
Aeronautical Computing Technique
关键词
复合材料
准静态压痕
损伤与检测
composite laminates
quasi-static indentation experiment
ultrasonic testing
