北京航空航天大学学报 ›› 1998, Vol. 24 ›› Issue (5): 551-554.

• 论文 • 上一篇    下一篇

复合材料蜂窝夹芯板低速冲击后的压缩

程小全, 寇长河, 郦正能   

  1. 北京航空航天大学 飞行器设计与应用力学系
  • 收稿日期:1997-09-10 发布日期:2010-11-18
  • 作者简介:31岁 博士生 100083 北京
  • 基金资助:

    航空科学基金(95B51066)资助项目

Compression of Composite Honeycomb Core Sandwich Panels after Low Velocity Impact

Cheng Xiaoquan, Kou Changhe, Li Zhengneng   

  1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics
  • Received:1997-09-10 Published:2010-11-18

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.

Abstract: 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.

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