大容量推进剂贮箱液体晃动性能试验  

Experiment of Liquid Sloshing Performance in Bulky Propellant Tank

作　　者：胡齐[1,2] 李永[1,2] 姚灿[1,2] 刘锦涛[1,2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]北京市高效能及绿色宇航推进工程技术研究中心,北京100190

出　　处：《空间控制技术与应用》2016年第3期44-48,共5页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(51406010)

摘　　要：对某种内带推进剂管理装置(PMD)的大容量推进剂贮箱内液体晃动性能进行试验.开展不同充液比工况下空壳贮箱液体晃动试验,分析比较晃动试验结果与采用等效动力学模型的液体晃动理论计算结果,两者结果一致吻合,试验系统可靠性和理论模型的正确性得到良好验证.然后开展了不同充液比工况下内带PMD贮箱液体晃动试验,试验结果表明贮箱内液体晃动性能受内部PMD结构影响明显.该试验研究结果为运载火箭和卫星的姿态和轨道控制系统的设计优化提供重要参考和数据支撑.Aiming at the bulky propellant tank with propellant management device （PMD） , experiment research on liquid sloshing performance is carried out. The liquid sloshing tests in a tank without PMD are developed under different liquid filling ratios. Based on the equivalent mechanical model, the theoretical result of liquid sloshing is calculated. The results of tests and calculation are analyzed and compared. The results are consistent, both the reliability of test system and the validity of theoretical model are well verified. Then the liquid sloshing tests in the tank with PMD are developed under different liquid filling ratios, and the test results indicate that the structure of inner PMD significantly affects the performance of liquid sloshing in the tank. All the experiment research results provide an important reference and data support for designing and optimizing the attitude and orbit control system of rocket and spacecraft.

关 键 词：液体晃动 晃动频率 阻尼 大容量推进剂贮箱 推进剂管理装置(PMD) 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]