一种航天器蜂窝夹层板发泡胶减重方法

针对航天器蜂窝夹层板发泡胶减重需求，以预埋件-发泡胶组合体等效半径为参数进行理论分析，给出蜂窝夹层板应力分布解析式，预测其破坏模式。据此提出两种发泡胶减重填充方案，并开展试件拉脱力测试、仿真，舱板组件性能评估和结构精度稳定性分析等验证工作。研究表明，方案1实现预埋件发泡胶减重25%，方案2实现减重50%。减重方案已成功应用于两型卫星，可为其它航天器研制提供有益的参考。

A Method of Foam Weight Reduction for Spacecraft Honeycomb Sandwich Panel

According to the foam weight reduction requirement of the honeycomb sandwich panel on the spacecraft, the equivalent radius of the mosaic foam assembly is used as the theoretical analysis parameter, and the analytical formula of stress distribution of the honeycomb sandwich panel is obtained to predict its failure mode. Based on this, two kinds of foam weight reduction filling schemes are proposed, and the tensile force test and simulation of specimens, performance evaluation of cabin board components and stability analysis of structural accuracy are carried out. The results show that the schemes 1 and 2 can achieve 25% and 50% weight reduction respectively. The weight reduction schemes have been successfully applied to two types of satellites, which can provide useful reference for other spacecraft development.