边界条件对复合材料层合板准静态压痕损伤的影响

摘要

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。%Composite laminates are riveted to the metal frame when applied on aircrafts,hence the boundary condition of composite laminates is four-edge clamped.Based on the real application,the differences of quasi-static indentation damage of the composite laminates with the four edges clamped simply supported were systemically compared from four aspects:delamination propagation mode,contact force,dent depth and damage width.The experimental results show that all these four aspects are different when composite laminates are loaded under different boundary conditions.Also the results can provide experimental data for investigating the quasi-static indentation damage of composite laminates on the basis of real application.