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基于Surface Evolver的推进剂贮箱气液界面分析
引用本文:姜志杰,吴宗谕,刘常青,黄奕勇,韩伟.基于Surface Evolver的推进剂贮箱气液界面分析[J].空间科学学报,2020,40(6):1066-1073.
作者姓名:姜志杰  吴宗谕  刘常青  黄奕勇  韩伟
作者单位:1. 军事科学院国防科技创新研究院 北京 100071;
基金项目:中国科学院前沿科学重点研究计划项目
摘    要:推进剂贮箱是航天器系统的重要部件,用于实现推进剂的管理与输运.在空间微重力条件下,贮箱内部液面呈弯曲状,掌握其液面分布特性是保证贮箱正常工作的前提.针对球形推进剂贮箱,采用Surface Evolver软件对其内部气液自由界面分布特性展开研究,分析充液比、接触角、Bond数等参数对贮箱液面的影响,得到液面分布随各参数的变化规律.研究结果表明,球形贮箱液面曲率随充液比的增大而增大,随接触角或Bond数的增大而减小.研究结果有助于实现推进剂贮箱液面快速分析,为贮箱及推进剂管理装置设计提供参考. 

关 键 词:推进剂贮箱    气液界面    微重力    Surface  Evolver
收稿时间:2020-09-27

Liquid-gas Interface Analysis of Propellant Tank Based on Surface Evolver
Institution:1 National Innovation Institute of Defense Technology, Chinese Academy of Military Science, Beijing 100071;2 College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073;3 China Aerodynamics Research and Development Center, Mianyang 621000)
Abstract:Propellant tank is an important part of spacecraft system, which is used for the management and transportation of propellant. Under the microgravity condition, the liquid-gas interface inside the propellant tank is curved. The investigation of the liquid-gas interface distribution characteristics is the premise to ensure the normal operation of the propellant tank. In this paper, Surface Evolver, an open-source surface evolution analysis software, is used to study the distribution characteristics of liquid-gas interface in spherical propellant tanks. The influences of filling ratio, contact angle, Bond number and other parameters on the liquid-gas interface are analyzed emphatically, and the variation law of the liquid-gas interface distribution in the propellant tank with each parameter is obtained. The results show that the shape of the liquid-gas interface of the spherical tank is more curved with the increase of the liquid filling ratio, and more flat with the increase of the contact angle or Bond number. Rapid analysis of the liquid-gas interface of the propellant tank is realized, which can provide guidance for the design of the propellant tank and the propellant management device. 
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