变轨条件下卫星贮箱内液体推进剂晃动特性三维数值模拟  

Numerical Simulation of Characteristics on Liquid Sloshing in Tank of Spacecraft During Orbital Transfer

作　　者：张博譞[1] 李国岫[1] 虞育松[1] 

机构地区：[1]北京交通大学机电学院,北京100044

出　　处：《上海航天》2014年第5期12-16,53,共6页Aerospace Shanghai

基　　金：国家自然科学基金资助项目(51076008);中央高校基本科研业务费专项资金资助

摘　　要：以某卫星液体推进剂贮箱为研究对象,用Fluent三维数值模拟软件,对在零重力环境变轨过程中贮箱内液体推进剂的晃动特性进行数值模拟。分析了晃动过程中液体推进剂的质心变化和液体推进剂对贮箱的作用力。数值模拟获得了液体推进剂在变轨过程中晃动的频率和阻尼比。与ABRAMSON等根据实验结果拟合得出的阻尼比经验公式计算结果和文献中对阻尼比的简化计算结果相比,模拟结果接近经验公式,同时能反映阻尼比随液深的变化,计算结果具有可信度。The liquid propellant of some satellite was served as the object in this paper. The characteristics of liquid sloshing in tank during the orbital transfer in the zero gravity environment was simulated by Fluent 3D numerical software. The centroid change of the propellant and force of the liquid propellant on the tank during the sloshing were analzed. The sloshing frequency and damping ratio of liquid propellant during the transfer was gained by simulation. The simulation results was approaching with the result calculated by experience formula in value when it compared the results calculate through the experience fitting formula derived by Abramson and the damping ratio of the simplified calculation in the reference, and it could reflect the damping ratio changes with the fluid depth. The result from simulation was credibility.

关 键 词：变轨过程 液体燃料晃动 阻尼比 数值模拟 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]