摘要
蜂窝夹层结构镶嵌件是航天器结构中广泛应用的连接部件,其设计是否合理直接影响着航天器结构设计的好坏。为了得到镶嵌件受垂直于面板的拉伸载荷时的具体受力情况,按照蜂窝夹层结构镶嵌件的实际结构形式建立其有限元模型进行了计算分析。结果得出,镶嵌件承受垂直于面板的拉伸载荷时,蜂窝芯子是决定镶嵌件拉伸承载力的关键因素,其中,蜂窝芯子中的单层箔壁最先破坏。在此基础上,分析了芯子高度、密度及面板厚度对镶嵌件拉伸承载力的影响,提出了通过在镶嵌件周围局部加密蜂窝芯子提高镶嵌件拉伸承载力的措施。
Honeycomb sandwich panel inserts are widely used in aerospace structures.In order to get the load transfer performance of inserts under pulls-out loads,a finite element analysis model for the inserts has been built according to the structure in detail and the analysis has been conducted.The results show that insert failure loads under pull-out loads are limited by strength of the core,and this failure happens firstly in the thinnest wall of the core.Furthermore,a parametric study has been conducted with respect to core height,density and face sheet thickness.An effective measure of improving the pull-out load limitation of inserts has been suggested by increasing the core density around the inserts.
出处
《空间电子技术》
2012年第1期35-38,62,共5页
Space Electronic Technology
关键词
镶嵌件
拉伸承载力
有限元分析
Insert
Pull-out strength
Finite element analysis
