空间柔性充气密封舱用新型填充防护结构碎片撞击计算分析与实验研究

为实现空间柔性充气密封舱在轨对空间碎片的防护需求，设计了一种以玄武岩纤维布和Kevlar纤维布填充的多层柔性防护结构。应用Christiansen撞击极限方程对Nextel/Kevlar填充防护结构在不同结构参数下的撞击极限进行计算分析，得出了防护层总间距、Nextel纤维布层数和Kevlar纤维布层数对防护结构撞击极限的影响特性，为柔性防护结构强重比的优化设计提供了依据。利用二级轻气炮对玄武岩/Kevlar纤维布填充防护结构进行超高速撞击实验研究，获取了防护结构在低速区、高速区和超高速区的撞击数据，并以Nextel/Kevlar填充防护结构撞击极限计算曲线为参照对实验结果进行分析，验证了玄武岩/Kevlar纤维布填充防护结构可对空间柔性充气密封舱起到防护空间碎片撞击的效果。

Impact limit calculation and experimental study of a novel preventive filled structure used in space flexible inflatable sealed cabin

In order to protect the space flexible inflatable sealed cabin from the space debris impact in orbit, a multi-layer flexible protective structure filled with layers of Basalt fiber cloth and Kevlar fiber cloth is proposed. The impact limit of the Nextel/Kevlar fiber cloth filled protective structures with different structural parameters is simulated and analyzed based on the Christiansen impact limit equation, including the influencing factors of the total spacing of the protective layers, as well as the number of the layers of the Nextel fiber cloth and the Kevlar fiber cloth. The results provide a basis for the optimal design of the strength-weight ratio of the protective structure. The hypervelocity impact test of the Basalt/Kevlar fiber cloth filled protective structure is carried out by using a two-stage light gas gun. The impact limit data of the protective structure in different speed zones are obtained, and the experimental results are compared with the impact limit simulation analysis curve. It is confirmed that the Basalt/Kevlar fiber cloth filled protective structure has adequate capability of debris protection for the space flexible inflatable sealed cabin.