Page 71 - 《真空与低温》2026年第2期

真空与低温 第 32 卷 第 2 期
190 Vacuum and Cryogenics 2026 年 3 月

微 重 力 下 低 温 贮 箱 热 力 学 排 气 系 统 参 数 分 析 及 性 能 优 化

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姚 磊 ，康馨月 ，闫春杰 ，王 琎 ，杨 鹏 1*
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（1. 西安交通大学能源与动力工程学院 热流科学与工程教育部重点实验室，西安 710049；
2. 兰州空间技术物理研究所 真空技术与物理重点实验室，兰州 730000）
摘要：为解决空间低温推进剂贮箱在微重力下的压力控制问题，实现低温推进剂的长期在轨运行，论文建立
了液氢贮箱自增压和热力学排气系统模型。研究了外界漏热作用下贮箱内的自增压过程，揭示了热分层现象的
形成机理。结合正交试验和 FLUENT 模拟，设计了 16 种不同参数组合工况，详细分析了循环泵流量、排气率、喷
嘴尺寸和节流阀背压对降压过程的影响，并量化了各参数的影响权重，以最小排气损失为目标，开展了参数优化
设计。结果表明：流量越大，平均压降时间越短；在流量相同的情况下，排气率越高，主流流体入口温度越低，压力
下降更快；在相同的排气量下，当喷嘴尺寸较小时，进气速度较快，降压时间越短。对排气量而言，参数重要性排
序为：排气率 > 循环泵流量 > 喷嘴尺寸 > 节流阀背压。由均值主效应图得到了各参数的最佳取值，循环泵流量为
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0.04 kg·s 、节流阀背压为 10 kPa、排气率为 1%、喷嘴直径为 0.005 m。本研究为 TVS 系统设计与控制提供了理论
依据，后续可开展实验验证与动态工况适用性研究。
关键词：热力学排气系统；液氢；微重力；压力控制
中图分类号：TB657；TK172 文献标志码：A 文章编号：1006-7086（2026）02-0190-09
DOI：10.12446/j.issn.1006-7086.2026.02.010

Parameter Analysis and Performance Optimization of Thermodynamic Vent System in
Cryogenic Tanks under Microgravity

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YAO Lei ，KANG Xinyue ，YAN Chunjie ，WANG Jin ，YANG Peng 1*
（1. Key Laboratory of Thermo-Fluid Science and Engineering of MOE，School of Energy and Power Engineering，
Xi’an Jiaotong University，Xi’an 710049，China；2. Science and Technology on Vacuum
Technology and Physics Laboratory，Lanzhou Institute of Physics，Lanzhou 730000，China）
Abstract：To address the pressure control challenges in space cryogenic propellant tanks and achieve long-term on-orbit
operation of cryogenic propellants under microgravity conditions，this study developed a self-pressurization model and a ther-
modynamic vent system （TVS） model for liquid hydrogen. The self-pressurization process in the liquid hydrogen tank under
the influence of external heat leakage was studied. The formation mechanism of the thermal stratification phenomenon was
revealed. By integrating orthogonal experimental design and FLUENT simulations， a total of 16 operating conditions with
distinct parameter combinations were configured when TVS started to work. The effects of circulation pump flow rate，ex-
haust venting rate，nozzle size，and throttle valve backpressure on the pressure reduction process were analyzed. The influ-
ence weight of each parameter was quantified. With the goal of minimizing exhaust mass，a parameter optimization design
was conducted. The results indicate that increasing the circulation pump flow rate can shorten the pressure reduction time.
Under identical circulation pump flow rate conditions，a higher exhaust venting rate leads to lower inlet temperature of the
main fluid stream and more rapid depressurization process. For the same exhaust venting rate，smaller nozzle sizes result in
greater inlet velocity and shorter pressure reduction time. In terms of exhaust mass，the parameter significance ranking is: ex-
haust venting rate > circulation pump flow rate > nozzle size > throttle valve backpressure. The optimal values of each param-
eter were determined through analysis of the mean main effect plots. The optimal operating parameters were as follows: cir-
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culation pump flow rate of 0.04 kg·s ， throttle valve backpressure of 10 kPa， venting rate of 1%， and nozzle diameter of

收稿日期：2025−12−30
基金项目：民用航天技术预先研究项目（D010302）
作者简介：姚磊，硕士研究生。E-mail：392561221@qq.com
通信作者：杨鹏，副教授，博士生导师。E-mail：yp2019@mail.xjtu.edu.cn