摘要
基于低速冲击后复合材料蜂窝夹芯板压缩破坏机理的实验研究，用当量分层来模拟Ｎｏｍｅｘ蜂窝夹芯板的低速冲击损伤，假设当量分层区子层板的边界为固支，并且认为子层板失稳时夹芯板所承受的载荷为压缩破坏载荷．将计算结果与实验结果进行比较，表明了对面板无明显断裂的低速冲击损伤情况，用损伤当量法计算蜂窝夹芯板的剩余压缩强度是可行的．
Based on the experimental study of compressive failure mechanisms on composite honeycomb core sandwich panels after low speed impact before, a equivalent delamination was used to replace the low speed impact damage of Nomex honeycomb core sandwich panels in this paper. It was postulated that the edge of sublaminate formed by the equivalent delamination is clamped. The load on which the sublaminate buckled was considered to be compressive failure load. Comparing the results of theory with experiment, it showed that the method of equivalent damage could be used to predict the residual compressive strength of honeycomb core sandwich panels, in the case that the facesheet of sandwich panels had no obvious cracks after low speed impact.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1998年第5期555-558,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
