【作者】 李光亮； 郑锡涛； 郑晓霞； 杜兴刚；

【Author】 Li Guangliang,Zheng Xitao,Zheng Xiaoxia,Du Xinggang (Schools of Aeronautics,Northwestern Polytechnical University,Xi’an 710072)

【机构】 西北工业大学航空学院；

【摘要】 复合材料泡沫芯夹层结构是飞行器中常用的结构形式,但其层间性能和抵抗低速冲击性能较弱,在低速冲击荷载的作用下,会造成面板基体开裂和纤维断裂、面板和芯材间的界面脱胶等多种形式的损伤,导致服役期间结构承载能力的下降。本文用大型有限元软件ABAQUS模拟泡沫芯夹层结构冲击后的损伤面积,模拟结果与实验结果相一致,证明了模拟方法的可行性。同时为了找出影响损伤面积的因素,本文还模拟了不同面板厚度、不同泡沫芯厚度和不同能量下的损伤面积,本文结论为改进复合材料泡沫芯夹层结构分析与设计提供了有效方法。更多还原

【Abstract】 Foam core-based sandwich composite is frequently used in the aerocraft industry,however,the delamination and poor resistance under impact are the main drawbacks,especially under the low-velocity impact,it will cause the matrix cracking, fiber breaking, skin-core debonding,etc. , which will lead performance to descend. Therefore,it’s necessary to study the damage after the low-velocity impact. In this paper,a commercial finite element software ABAQUS was used to predict the damage areas of composite sandwich structure after low-velocity impact. Besides,other things,such as the thickness of the composite panel,the thickness of foam core,the impact energy has been taken into consideration. By analysis,the numerical simulate results have good agreement with the experimental results obtained,which proves the correctness of the model. The results also offer evidence for the analysis and design of the improved composite sandwich structure.更多还原