边界条件对复合材料层合板准静态压痕损伤的影响

在实际的服役过程中,飞机用复合材料层合板通过四边铆接的方式与飞机金属框架进行连接,其受力时的边界条件为四边固支。以实际应用背景为基础,分别从分层损伤扩展模式、接触力、凹坑深度、损伤宽度四个方面系统地比较了四边固支和四边简支两种边界条件下,复合材料层合板准静态压痕损伤的区别。结果表明以上四种变量在两种边界条件下均存在明显差异,可为基于实际应用的复合材料准静态压痕损伤研究提供实验依据。

The influence of boundary conditions on the quasi-static indentation damage of composite laminates

Carbon fiber/bismaleimide composite laminates are riveted to the metal frame when applied on aircrafts, hence the boundary condition of composite laminates is four edges clamped. Based on the real application, in this study, the differences of quasi-static indentation damage of composite laminates under four edges clamped and under simply supported were systemically compared from four aspects: delamination propagation, contact force, dent depth and damage width. The experimental results showed that all these four aspects were different when composite laminates were under different boundary conditions. Also the results provided experimental data for investigating quasi-static indentation damage of composite laminates based on real application.