Lattice structures offer enhanced stiffness-to-weight characteristics for structures in highly mass sensitive applications like aviation and aerospace. The adaptability of composite materials allows for further optimisation of the structural layout of the lattice to reduce mass for primary aerospace structures. The attachment point on the lattice is a key structural feature, defining the interaction between the payload and the primary structure. The present work investigates an attachment point design for a lattice satellite central cylinder approximately 1.5 m in diameter, manufactured using composite prepreg fibre placement. This work presents the design, experimental testing and numerical analysis of attachment points consisting of filled patches in the lattice. The points were loaded in shear and the responses of the surrounding helical and hoop ribs of the lattice were monitored using strain gauges, LVDTs and a digital image correlation system. The measured response of the structure validated numerical predictions and the numerical design methodology.

晶格结构为航空和航天等对质量敏感的应用提供了增强的刚度-重量特性。复合材料的适应性允许进一步优化晶格的结构布局，以减少主要航空航天结构的质量。晶格上的附着点是关键的结构特征，它定义了有效载荷和主要结构之间的相互作用。本工作研究了直径约1.5 m的点阵卫星中心圆柱体的连接点设计，该中心点是使用复合预浸料纤维放置制成的。这项工作介绍了由点阵中填充的补丁组成的附着点的设计，实验测试和数值分析。将这些点加载到剪切机中，并使用应变仪，LVDT和数字图像相关系统监视晶格周围的螺旋形和箍筋的响应。结构的实测响应验证了数值预测和数值设计方法的有效性。