复合材料层合板低速冲击后压缩破坏的数值模拟  

Numerical Simulation of the Compressive Failure of Composite Laminates under Low Velocity Impact

作　　者：贾建东[1,2] 丁运亮[1] 胡伯仁[2] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016 [2]成都飞机工业(集团)公司技术中心,成都610092

出　　处：《机械科学与技术》2010年第10期1320-1324,共5页Mechanical Science and Technology for Aerospace Engineering

摘　　要：采用软化夹杂法来模拟低速冲击后层合板的压缩破坏。笔者用ABAQUS软件建立冲击损伤的有限元模型,模型将损伤区等效成一个圆形的软化夹杂,研究了不同的损伤深度对冲击后剩余压缩强度的影响;分析了层合板在压缩过程中,各单层的载荷分配情况;并且模拟了复合材料层合板从损伤开始到完全失去承载能力的压缩破坏全过程。计算结果表明:复合材料层合板冲击后的压缩破坏,损伤最早发生在冲击损伤区周围的±45°铺层,主要发生基体压缩损伤;在压缩载荷下,0°铺层主要的损伤形式是纤维的屈曲;90°铺层发生的主要损伤形式也是基体压缩损伤,但损伤的面积较小。The compressive failure of composite laminates after low-velocity impact has been simulated.The impact damage FEM model was built in ABAQUS software.In this model,the impact damage area is considered as a circular softening inclusion.The residual strength with different impact damage depth is studied.The load distribution of single layer is studied.The course of the compressive failure from damage onset to total destroy is simulated.The result shows that the damage first appears in ± 45° layers.The position is around impact damage area.The dominating damage mode is matrix compression.The dominating damage mode of 0° layers is fibre buckling.The damage mode of 90° layers is also matrix compression,but the damage area is small.

关 键 词：复合材料层合板 冲击损伤 有限元 剩余强度 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]