飞行器用液氢贮箱低温推进剂晃动热力学响应分析  

Analysis of Thermodynamic Response of Cryogenic Propellant Sloshing in Liquid Hydrogen Tank for Carrier Vehicle

作　　者：李文 陈叔平[1] 赵高逸 谢高峰 LI Wen;CHEN Shuping;ZHAO Gaoyi;XIE Gaofeng(School of Petrochemical Engineering,Lanzhou University of Technology,Lanzhou 730050,China;Beijing Institute of Space Launch Technology,Beijing 100076,China)

机构地区：[1]兰州理工大学石油化工学院,兰州730050 [2]北京航天发射技术研究所,北京100076

出　　处：《载人航天》2022年第6期771-778,共8页Manned Spaceflight

摘　　要：研究飞行器低温推进剂贮箱内流体晃动的热力耦合特性,采用计算流体力学(CFD)技术仿真不同工况对液氢贮箱内低温推进剂晃动热力学的影响。考虑外部环境漏热和气液界面相变对贮箱气枕压力的影响,并通过用户自定义函数(UDF)将外部晃动激励施加于罐壁作为动量边界,利用VOF法捕捉气液相界面波动。结果表明:晃动激励越大,气枕空间压降越大,晃动激励为0 m/s、0.11 m/s、0.22 m/s、0.44 m/s时的气枕最大压降分别是2 Pa、120.3 Pa、6084.5 Pa、9158.3 Pa;气枕压降随初始液体温度的降低而增大,初始液体温度为20.0 K、21.0 K、21.5 K时的气枕压降时为6079 Pa、5248 Pa、3902 Pa;初始充满率越高,气枕压降越大,充满率为30%、40%、50%、60%、70%时气枕压降分别是1905 Pa、3758 Pa、6085 Pa、6476 Pa、8339 Pa。流体晃动扰动了液氢贮箱内气液界面处的热力学平衡,导致气枕压力大幅降低,为保证飞行器的稳定运行需采取合理的增压或防晃措施来维持贮箱气枕压力。Targeting the problem of the cryogenic propellant sloshing of the carrier vehicle,computational fluid dynamics(CFD)technology was used to simulate and study the effects of different operating conditions on the thermodynamics of the cryogenic propellant sloshing in the liquid hydrogen tank for carrier vehicle so as to study the thermal coupling characteristics of the fluid sloshing in the tank.The influence of the external environment heat leakage and the phase change of the gas-liquid interface on the ullage pressure in the tank were taken into account during the calculation.The external sloshing excitation was applied to the tank wall as the momentum boundary through a user-defined function(User Defined Function,UDF),and the VOF method combined with Mesh Motion settings was used to track the gas-liquid interface.The study found that the greater the sloshing excitation,the greater the pressure drop in the ullage.When the sloshing excitation were 0 m/s,0.11 m/s,0.22 m/s,and 0.44 m/s,the pressure drop of the ullage were 2 Pa,120.3 Pa,6084.5 Pa,9158.3 Pa respectively.The ullage pressure drop increased with the decrease of the initial liquid temperature.When the initial liquid temperature were 20.0 K,21.0 K,21.5 K,the ullage pressure drop were 6079 Pa、5248 Pa、3902 Pa,respectively.The higher the initial full rate,the greater the ullage pressure drop.When the full rate were 30%,40%,50%,60% and 70%,the ullage pressure drop were 1905 Pa、3758 Pa、6085 Pa、6476 Pa、8339 Pa,respectively.Fluid sloshing disturbed the thermodynamic balance at the gas-liquid interface in the liquid hydrogen tank,resulting in a significant reduction in the pressure of the ullage.To ensure the stable operation of the carrier vehicle,reasonable pressurization or anti-sloshing measures should to be taken to maintain the pressure of the ullage in the tank.

关 键 词：晃动激励 低温推进剂 数值模拟 液氢贮箱 飞行器 

分 类 号：TK19[动力工程及工程热物理—热能工程]