摘要
对含低速冲击损伤的Ｎｏｍｅｘ蜂窝夹芯板试件进行了压缩实验，用Ｘ光技术、热揭层技术和外观检测等对压缩破坏损伤发展的过程进行了研究，分析了压缩破坏机理，结果表明：剩余压缩强度随冲击能量的增加而减少；夹芯板的压缩破坏主要由前面板控制，前面板发生局部屈曲的载荷与板的压缩破坏载荷几乎相等；表面玻璃布不仅能减少冲击损伤，而且能使板内的损伤显露在表面，容易让人发现．
Compressive tests after low velocity impact were carried out on Nomex honeycomb core sandwich specimens. Some methods were used to study the cause of damage development when the specimens were compressed to fail: X ray, deply, and visual inspection. Compressive failure mechanism was analyzed. The results showed that the residual compressive strength decreased while impact energy increased. The compressive failure of Nomex honeycomb core sandwich specimen was controlled by the front facesheet.The loads that caused the front facesheets to buckle was close to the load that made the planes fail. The glass cloth on surface not only could reduce impact damage, but also could show the damage within the plane on the surface so that it could been found easily.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1998年第5期551-554,共4页
Journal of Beijing University of Aeronautics and Astronautics
基金
航空科学基金
关键词
蜂窝结构
损伤
压缩强度
低速冲击
复合材料
honeycomb structure
injuries
compressive strength
low velocity impact
