用于航天器贮箱的复合材料层合板低速冲击损伤及其渗漏规律研究  

Study on Low-Velocity Impact Damage and Leakage Law of Composite Laminates for Spacecraft Tanks

作　　者：顾佳辉 杨子涵 刘德博 崔浩 赵振强[1,3] GU Jiahui;YANG Zihan;LIU Debo;CUI Hao;ZHAO Zhenqiang(School of Aeronautics,Northwestern Polytechnical University,Xi an 710072,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;Shaanxi Key Laboratory of Impact Dynamics and its Engineering Applications,Xi an 710072,China;School of Civil Aviation,Northwestern Polytechnical University,Xi an 710072,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]北京宇航系统工程研究所,北京100076 [3]陕西省冲击动力学及工程应用重点实验室,西安710072 [4]西北工业大学民航学院,西安710072

出　　处：《宇航总体技术》2023年第3期35-43,共9页Astronautical Systems Engineering Technology

基　　金：国家自然基金航天联合基金(U1837204)。

摘　　要：得益于优异的力学性能和减质优势,贮箱复合材料化已成为新一代航天器的重要特征之一,而复合材料贮箱的冲击后渗漏问题须要重点关注。针对一种用于航天器贮箱的含表层机织布复合材料层合板,通过依次开展低速冲击试验、C扫描损伤检测和氦质谱渗漏检测,获取不同能量冲击后层合板的内部分层损伤和渗漏率,并对比分析了机织布分别置于冲击侧和背侧时层合板的渗漏规律。结果表明,将机织布层置于冲击背侧时,层合板的冲击渗漏门槛值显著提高,且发生渗漏时出现目视可见损伤。The composite tanks have been used in the new generation of spacecraft because of their excellent mechanical performance and weight reduction advantages.However,the post-impact leakage of composite tanks is of particular concern.In this paper,the post-impact leakage performance of a composite laminate with a surface woven layer is investigated through carrying out successively the low-velocity impact test,C-scanning technology and helium mass spectrometry leakage detection.The delamination range and leakage rates of the composite laminates after different energy impact were obtained,and the leakage performance was compared and analyzed when the woven fabric was placed on the impact side and the back side,respectively.The results show that when the woven layer is placed on the back side,the impact leakage threshold of the laminate is significantly increased,and the visual damage can be found when the leakage occurs.

关 键 词：复合材料层合板 航天器贮箱 冲击方向 渗漏门槛值 

分 类 号：V41[航空宇航科学与技术—航空宇航推进理论与工程]