负过载下多孔隔板对液氧贮箱蓄液性能的影响研究

doi:10.11949/0438-1157.20241369

摘要/Abstract

摘要：

以典型运载器的液氧贮箱为研究对象，基于流体体积（VOF）法构建了监测气液界面的三维CFD仿真模型，采用该模型对不同孔板布置情况、不同初始液面状态、不同负过载程度下液氧流动行为进行模拟，对比了各工况液氧离开贮箱底部和气体下潜两种行为特性。多孔隔板可以有效降低液氧离开贮箱底部的流量，-0.20g负过载条件下流量减少95.63%；且该流量与负过载程度呈正相关。气体下潜速度受气泡形态与负过载程度等因素共同影响，当推进剂填充率为50.18%且发生10°倾斜的贮箱受到-0.20g负过载时，会形成气液循环通道使气泡迅速长大，有效下潜速度可达0.317 m/s，甚至大于负过载为-0.40g但贮箱不倾斜时的气体下潜速度。因此设计孔板位置时应综合考虑推进剂余量、箭体姿态和负过载程度等因素。

关键词: 液氧, 负过载, 多孔隔板, 气体下潜, 流体动力学, 气液两相流, 数值模拟

Abstract:

In comparison to single-use launch vehicles, reusable launch vehicles (RLV) are gaining significant attention due to their high efficiency, low cost, and broad application scope. However, their unique flight profiles also subject them to more complex variations in g-loading, such as axial negative gravity experienced by lower stage during specific flight phases, presenting new technical challenges in propellant management. Existing studies highlight the unique advantages of perforated plates in managing propellant under negative gravity. Consequently, this paper explores the liquid retention capabilities of perforated plates from multiple perspectives. The present study focuses on the liquid oxygen (LO _X ) tank of a typical launch vehicle. A three-dimensional CFD simulation model, based on the volume of fluid (VOF) method, was constructed to capture the gas-liquid interface. Using this model, the LO _X flow behavior was simulated under different perforated plate arrangements, different initial liquid conditions and varying negative gravity. The retention effect of perforated plate was analyzed from two perspectives: the upward ejection of LO _X and the downward movement of O₂ bubbles. The results of this study indicate that perforated plate can effectively prevent LO _X upward ejection, reducing the outflow by 95.63% under a -0.20g negative gravity; additionally, the outflow rate of liquid oxygen is positively correlated with the degree of negative gravity. The influence on liquid oxygen outflow is negligible when the liquid level is above or below the perforated plate and remains horizontal; however, when the liquid level is inclined, a rapid and significant outflow of liquid oxygen occurs due to the gas-liquid circulation channels above and below the perforated plate. The submergence speed of gas is influenced by both the morphology of bubbles and the degree of negative gravity. When the propellant fills up to the height of the perforated plate and the vehicle, tilted at 10°, is subjected to a -0.20g negative gravity, the bubbles grow rapidly, reaching an effective submergence speed of 0.317 m/s. This speed exceeds that observed under a -0.40g negative gravity with a horizontal liquid level. Therefore, the arrangement of the perforated plate should comprehensively consider factors such as volume of remaining propellant, rocket gimbal angle, and degree of negative overload.

Key words: liquid oxygen, negative gravity, perforated plates, gas submergence, hydrodynamics, gas-liquid flow, numerical simulation

中图分类号:

TK 05

曹庆泰, 郭松源, 李建强, 蒋赞, 汪彬, 耑锐, 吴静怡, 杨光. 负过载下多孔隔板对液氧贮箱蓄液性能的影响研究[J]. 化工学报, 2025, 76(S1): 217-229.

Qingtai CAO, Songyuan GUO, Jianqiang LI, Zan JIANG, Bin WANG, Rui ZHUAN, Jingyi WU, Guang YANG. Numerical study on influence of perforated plate on retention performance of liquid oxygen tank under negative gravity[J]. CIESC Journal, 2025, 76(S1): 217-229.

图/表 29

图1 垂直起降（VTVL）可复用运载器典型飞行剖面

Fig.1 Typical flight profile of a vertical takeoff and landing (VTVL) reusable carrier

图2 一、二级分离段级间分离时序

Fig.2 Timing sequence of interstage separation of the upper stage and lower stage of a rocket

图3 贮箱内流域（a）及多孔隔板（b）结构示意图

Fig.3 Schematic diagram of the structure of LO X tank (a) and perforated plate (b)

图4 网格划分情况

Fig.4 Grid details

表1 计算工况汇总

Table 1 Summary of working conditions

工况	负过载/(m/s²)	孔板布置情况	液面初始化情况	填充率/%	液面坐标描述
对照组	-0.20g	无多孔隔板	水平液面，位于正常情况的位置	50.18	z=602 mm
工况1	-0.20g	有多孔隔板	水平液面，高于孔板中截面30 mm	52.68	z=632 mm
工况2	-0.20g	有多孔隔板	水平液面，低于孔板中截面30 mm	47.68	z=572 mm
工况3	-0.20g	有多孔隔板	液面倾斜10°，液面中心位于孔板中截面上	50.18	z=(tan10°)x + 602 mm
工况4	-0.03g	有多孔隔板	水平液面，与孔板中截面重合	50.18	z=602 mm
工况5	-0.10g	有多孔隔板	水平液面，与孔板中截面重合	50.18	z=602 mm
工况6	-0.20g	有多孔隔板	水平液面，与孔板中截面重合	50.18	z=602 mm
工况7	-0.40g	有多孔隔板	水平液面，与孔板中截面重合	50.18	z=602 mm

图5 各工况初始条件和边界条件汇总示意图

Fig.5 Summary of initial and boundary conditions

表2 液氧和氧气的物性参数

Table 2 Physical properties of liquid and gas oxygen

物性参数	液氧	氧气
密度/(kg/m³)	1142.70	5.34
动力黏度/(Pa·s)	2.032×10^-4	1.785×10^-5

图6 实验结果与本文模型仿真结果对比

Fig.6 Comparison between the experimental results and the simulation results of the model in present study

图7 水平方向质心位置验证

Fig.7 Verification of center of mass position in horizontal direction

表3 不同网格数下的质心轴向位置

Table 3 Axial position of center of mass for different number of meshes

网格数量/个	质心轴向位置/m
网格数量/个	t=0.5 s	t=1.0 s	t=1.5 s	t=2.0 s	t=2.5 s	t=3.0 s	t=3.5 s
190万	0.316329	0.316900	0.321874	0.333099	0.347278	0.359630	0.370671
244万	0.316330	0.316864	0.321895	0.331798	0.343617	0.359207	0.373889
326万	0.316339	0.316937	0.321092	0.328244	0.337817	0.351348	0.361177

图8 对照组（无隔板，水平初始液面，液氧初始填充率50.18%，负过载-0.20g）液氧流动行为

Fig.8 Liquid oxygen flow behavior of control group (no perforated plate, horizontal initial liquid level with 50.18% initial liquid oxygen fill rate, -0.20g)

图9 工况6（有隔板，水平初始液面，液氧初始填充率50.18%，负过载-0.20g）液氧流动行为

Fig.9 Liquid oxygen flow behavior in Case 6 (with perforated plate, horizontal initial liquid level with 50.18% initial liquid oxygen fill rate, -0.20g)

图10 有无隔板时关键参数对比

Fig.10 Comparison of key parameters with and without the perforated plates

图11 对照组和工况6中不同时刻的气体下潜深度

Fig.11 Depth of gas dive at different moments in the control group and Case 6

图12 工况1（有隔板，水平初始液面，液氧初始填充率52.68%，负过载-0.20g）液氧流动行为

Fig.12 Liquid oxygen flow behavior in Case 1 (with perforated plate, horizontal initial liquid level with 52.68% initial liquid oxygen fill rate, -0.20g)

图13 工况2（有隔板，水平初始液面，液氧初始填充率47.68%，负过载-0.20g）液氧流动行为

Fig.13 Liquid oxygen flow behavior in Case 2 (with perforated plate, horizontal initial liquid level with 47.68% initial liquid oxygen fill rate, -0.20g)

图14 工况3（有隔板，倾斜初始液面，液氧初始填充率50.18%，负过载-0.20g）液氧流动行为

Fig.14 Liquid oxygen flow behavior in Case 3 (with perforated plate, inclined initial liquid level with 50.18% initial liquid oxygen fill rate, -0.20g)

图15 不同初始液面条件的关键参数

Fig.15 Comparison of key parameters for different initial liquid level conditions

图16 工况1和工况3孔板附近流动情况对比

Fig.16 Comparison of flow near the perforated plate for Case 1 and Case 3

图17 工况1以及工况6中的蘑菇状气泡

Fig.17 Mushroom-shape bubbles in Case 1 and Case 6

图18 各工况不同时刻气体下潜深度

Fig.18 Depth of gas dive at different moments in the Case 1, Case 2 and Case 3

图19 工况4（有隔板，水平初始液面，液氧初始填充率50.18%，负过载-0.03g）液氧流动行为

Fig.19 Liquid oxygen flow behavior in Case 4 (with perforated plate, inclined initial liquid level with 50.18% initial liquid oxygen fill rate, -0.03g)

图20 工况5（有隔板，水平初始液面，液氧初始填充率50.18%，负过载-0.10g）液氧流动行为

Fig.20 Liquid oxygen flow behavior in Case 5 (with perforated plate, inclined initial liquid level with 50.18% initial liquid oxygen fill rate, -0.10g)

图21 工况7（有隔板，水平初始液面，液氧初始填充率50.18%，负过载-0.40g）液氧流动行为

Fig.21 Liquid oxygen flow behavior in Case 7 (with perforated plate, inclined initial liquid level with 50.18% initial liquid oxygen fill rate, -0.40g)

图22 不同负过载程度下的关键参数

Fig.22 Comparison of key parameters for different negative gravity

表4 不同负过载工况最终0.5 s质心的轴向移动速度

Table 4 Velocity of axial center of mass movement at the late stage of different negative gravity

负过载	质心轴向移动速度/(m/s)
-0.03g	2.05×10^-5
-0.10g	2.11×10^-3
-0.20g	1.75×10^-2
-0.40g	2.97×10^-2

图23 工况5~工况7中的蘑菇状气泡

Fig.23 Mushroom-shape bubbles in Case 5, Case 6 and Case 7

图24 各工况不同时刻气泡的下潜深度

Fig.24 Depth of gas dive at different moments in the Case 4, Case 5, Case 6 and Case 7

图25 各工况气体下潜有效速度对比

Fig.25 Comparison of effective velocity of gas dive for each case

参考文献 32

1	包为民. 可重复使用运载火箭技术发展综述[J]. 航空学报, 2023, 44(23): 8-33, 3.
	Bao W M. A review of reusable launch vehicle technology development[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 8-33, 3.
2	宋征宇, 黄兵, 汪小卫, 等. 重复使用航天运载器的发展及其关键技术[J]. 前瞻科技, 2022, 1(1): 62-74.
	Song Z Y, Huang B, Wang X W, et al. Development and key technologies of reusable launch vehicle[J]. Science and Technology Foresight, 2022, 1(1): 62-74.
3	容易, 刘辉, 于子文, 等. 可重复使用运载火箭返回段低温流体行为特性[J]. 航空学报, 2023, 44(23): 105-116.
	Rong Y, Liu H, Yu Z W, et al. Behavior of cryogenic propellant in return stage of reusable launch vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 105-116.
4	高朝辉, 刘宇, 肖肖, 等. 垂直着陆重复使用运载火箭对动力技术的挑战[J]. 火箭推进, 2015, 41(3): 1-6, 45.
	Gao Z H, Liu Y, Xiao X, et al. Challenge to propulsion technology for vertical landing reusable launch vehicle[J]. Journal of Rocket Propulsion, 2015, 41(3): 1-6, 45.
5	Zuo Z Q, Zhu W X, Huang Y H, et al. A review of cryogenic quasi-steady liquid-vapor phase change: theories, models, and state-of-the-art applications[J]. International Journal of Heat and Mass Transfer, 2023, 205: 123916.
6	Dodge F T. Fluid management in low gravity[M]//Low-Gravity Fluid Dynamics and Transport Phenomena. Washington D C: AIAA, 1990: 3-14.
7	尕永婧, 王浩苏, 张青松, 等. 垂直着陆过程推进剂流动行为特性及影响分析[J]. 深空探测学报, 2021, 8(1): 42-50.
	Ga Y J, Wang H S, Zhang Q S, et al. Propellant flow characteristics in tank and related impact analysis during the vertical landing stage[J]. Journal of Deep Space Exploration, 2021, 8(1): 42-50.
8	王晔, 张婉雨, 汪彬, 等. 多孔网幕泡破压力预测模型的建立及实验验证[J]. 化工学报, 2022, 73(3): 1102-1110.
	Wang Y, Zhang W Y, Wang B, et al. Analytical model of bubble point pressure for metal wire screens and experimental validation[J]. CIESC Journal, 2022, 73(3): 1102-1110.
9	Hartwig J W. Liquid Acquisition Devices for Advanced In-Space Cryogenic Propulsion Systems[M]. New York: Academic Press, 2016.
10	Himeno T, Watanabe T, Nonaka S, et al. Numerical and experimental investigation on sloshing in rocket tanks with damping devices[C]//43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. AIAA, 2007: AIAA2007-5557.
11	Chen L, Liu J T. Numerical simulation of fluid flow in the vane type tank on orbital refuelling process[J]. IOP Conference Series: Earth and Environmental Science, 2018, 163: 012085.
12	杨唱, 孙冰, 方杰. 航天器贮箱出流过程液体晃动及防晃[J]. 航空动力学报, 2018, 33(12): 3065-3072.
	Yang C, Sun B, Fang J. Liquid sloshing and anti-sloshing of spacecraft tank during outflow[J]. Journal of Aerospace Power, 2018, 33(12): 3065-3072.
13	Ohashi A, Furuichi Y, Haba D C, et al. Experimental and numerical investigation on pressure change in cryogenic sloshing with a ring baffle[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference. AIAA, 2017: AIAA2017-4760.
14	Liu Z, Li C. Influence of slosh baffles on thermodynamic performance in liquid hydrogen tank[J]. Journal of Hazardous Materials, 2018, 346: 253-262.
15	肖明堃, 黄永华, 吴静怡, 等. 非均匀磁场力作用下微重力液氧气液界面特性[J]. 制冷技术, 2020, 40(6): 1-11.
	Xiao M K, Huang Y H, Wu J Y, et al. Gas-liquid interface behavior of liquid oxygen in compensated microgravity field with inhomogeneous magnetic force[J]. Chinese Journal of Refrigeration Technology, 2020, 40(6): 1-11.
16	Hartwig J W. Propellant management devices for low-gravity fluid management: past, present, and future applications[J]. Journal of Spacecraft and Rockets, 2017, 54(4): 808-824.
17	Liu Z, Yuan K F, Liu Y L, et al. Fluid sloshing thermo-mechanical characteristic in a cryogenic fuel storage tank under different gravity acceleration levels[J]. International Journal of Hydrogen Energy, 2022, 47(59): 25007-25021.
18	Berglund M D, Bassett C E, Kelso J M, et al. The boeing delta Ⅳ launch vehicle—pulse-settling approach for second-stage hydrogen propellant management[J]. Acta Astronautica, 2007, 61(1/2/3/4/5/6): 416-424.
19	Space Exploration Technologies Corporation. SpaceX Demo Flight 2 Flight Review Update[EB/OL]. [2007-06-16]. .
20	Space Systems Engineering Website. The NEAR Rendezvous Burn Anomaly of December 1998[DS/OL]. [1999-11]. .
21	Hubert C. Behavior of spinning space vehicles with onboard liquids [R]. Technical Report, 2008: B8030.
22	Hartwig J, Esser N, Jain S, et al. CFD modeling of bidirectional PMDs inside cryogenic propellant tanks onboard parabolic flights[J]. Journal of Spacecraft and Rockets, 2024, 61(1): 296-312.
23	Varghese A P, Hartwig J W, Lieber S C, et al. Numerical design of a flow restrictor for tanked liquid nitrogen undergoing reduced-gravity flights[J]. Aerospace Science and Technology, 2024, 154: 109539.
24	Cheng G H, Jing W X, Gao C S. Recovery trajectory planning for the reusable launch vehicle[J]. Aerospace Science and Technology, 2021, 117: 106965.
25	Hirt C W, Nichols B D. Volume of fluid (VOF) method for the dynamics of free boundaries[J]. Journal of Computational Physics, 1981, 39(1): 201-225.
26	Morton K W. Numerical Methods for Fluid Dynamics[M]//Baines M J. New York: Academic Press, 1982: 273-486.
27	Guo S Y, Xiao M K, Xie F, et al. Optimization of helium consumption for feedback pressurization in liquid oxygen tanks[J]. International Journal of Heat and Mass Transfer, 2024, 230: 125739.
28	刘辉, 王亚军, 黄兵, 等. 推进剂重定位过程仿真与分析[J]. 南京航空航天大学学报, 2021, 53(S1): 17-24.
	Liu H, Wang Y J, Huang B, et al. Simulation and analysis of propellant reorientation process[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2021, 53(S1): 17-24.
29	Brackbill J U, Kothe D B, Zemach C. A continuum method for modeling surface tension[J]. Journal of Computational Physics, 1992, 100(2): 335-354.
30	陈虹, 高旭, 王向南, 等. 过冷液氧增压排液过程数值模拟研究[J]. 低温工程, 2023(1): 20-25, 36.
	Chen H, Gao X, Wang X N, et al. Numerical investigation on pressurization discharge of subcooled liquid oxygen[J]. Cryogenics, 2023(1): 20-25, 36.
31	Lemmon E W, Bell I H, Huber M L, et al. NIST Standard Reference Database 23: Reference Fluid Thermodynamic and Transport Properties-REFPROP, Version 10.0 [M]. Gaithersburg, 2018.
32	Salzman J, Masica W, Lacovic R. Low gravity reorientation in a scale-model Centaur liquid-hydrogen tank[R]. NASA, 1967.

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