Composite sandwich structures are commonly considered in large-scale aerospace applications due to their performance on a per mass basis. The nature of a large-scale sandwich structure generally necessitates the use of multiple sections of core to fill out the structural form. These core sections must be spliced together to ensure that shear loads are appropriately transmitted throughout the core. Because core installation in a large-scale component is a challenging operation, core splice joint width can be difficult to control in manufacturing. As such, the effects of core splice joint width on sandwich structure performance should be well understood. This study examines the effects of core splice joint width in honeycomb sandwich structures via mechanical testing and post-failure analysis. A threshold core splice joint width is shown to exist with respect to core shear, while the integrity of the facesheet-to-core interface is shown to degrade with increasing core splice joint width.

复合夹层结构因其按质量计算的性能而在大型航空航天应用中通常被考虑使用。大型夹层结构的性质通常需要使用多段芯材来填充结构形式。这些核心部分必须拼接在一起，以确保剪切载荷适当地传递到整个核心。由于在大型组件中安装磁芯是一项具有挑战性的操作，因此在制造过程中很难控制磁芯接头宽度。因此，应该很好地理解芯体拼接接头宽度对夹层结构性能的影响。本研究通过力学测试和失效后分析检查了蜂窝夹层结构中芯拼接接头宽度的影响。