Composite sandwich panels with lattice truss cores have dramatic static and dynamic characteristics, which are widely used in aerospace industry. Owing to the inability to sustain localized loads of joining, valid inserts are required to enable the interconnection of the sandwich panels. The present study develops a novel boundary insert parallel to the facesheets for pyramidal lattice truss core sandwich panels. Analytical-mechanical models are addressed for the proposed boundary insert subjected to in-plane pull-out, in-plane shear as well as out-of-plane shear loads and experimental tests are carried out to characterize mechanical behaviors. Failure sequences and mechanisms are discussed comprehensively and good correspondence is obtained with analytical prediction. Finite element simulation models are developed for visualization of internal load distribution. Experimental results show that significant improvements in load capacities can be achieved by the developed boundary insert compared with the interconnection concepts for honeycomb sandwich panels.

具有晶格桁架芯的复合夹芯板具有出色的静态和动态特性，已广泛用于航空航天工业。由于无法承受局部的连接载荷，因此需要有效的插件来实现夹心板的互连。本研究开发了一种新颖的边界插入物，该插入物平行于金字塔形桁架芯夹心板的面板。针对所提出的边界插入件在平面内拔出，平面内剪切以及平面外剪切载荷的情况下，建立了解析力学模型，并进行了实验测试以表征机械性能。全面讨论了故障序列和机理，并通过分析预测获得了良好的对应关系。开发了有限元仿真模型以可视化内部载荷分布。实验结果表明，与蜂窝夹芯板的互连概念相比，通过开发的边界插件可以显着提高负载能力。