Characteristics of pumping-back and propellant-refilling processes for diaphragm tank of space station
-
摘要:
针对增压气体复用式推进剂在轨补加方式的两大关键过程—贮箱抽气过程和推进剂加注过程的物理特性开展了研究，建立了膜盒贮箱抽气过程及补液过程的数学模型。仿真计算与地面试验的对比分析结果表明：抽气过程中贮箱气腔压力变化近似等温过程，气瓶压力变化近似指数为1.1的多变过程；加注过程中贮箱气腔压力变化近似等温过程。进一步对“和平号”空间站补加过程实例的仿真研究结果表明，膜盒贮箱抽气过程中高压气瓶中气体散热效果的强弱显著影响气瓶压力变化过程；膜盒贮箱加注过程中，随着气腔容积减小，贮箱压力上升速率将逐渐增大，由此导致加注速率在后期逐渐下降。
Abstract:Numerical models for a pumping-back process of pressurized gas and a propellant-refilling process of propellant tank were built, and the simulation results were compared with experimental data using pure water. It was found that the pressure variation of propellant tank in the pumping-back process and the refilling proces was similar to an isothermal process, and the pressure variation of pressurized gas-bottle in the pumping-back process was similar to a polytropic process with polytropic exponent of 1.1. Further simulation analysis was carried out with the developed model to investigate a typical propellant refueling process of the Mir Space Station, indicating that the pressure-rising rate of a pressurized gas-bottle in pumping-back proces was significantly influenced by heat dissipation of the pressurized gas-bottle, and the propellant-refilling rate of a tank descended gradually due to increase of the back pressure of the tank in a propellant-refilling process.
-
Key words:
- space station /
- propellant refueling /
- tank /
- gas-bottle /
- polytropic model
-
图 1 “和平号”空间站补加系统示意图
Figure 1. Sketch map of the propellant refueling system for the Mir Space Station
图 2 推进剂补加地面试验系统示意图
Figure 2. Sketch map of propellant refueling system for ground experiment
图 3 抽气过程贮箱气腔压力仿真与试验结果对比
Figure 3. Comparison of simulation results and experiment results of tank pressure in pumping-back process
图 4 抽气过程高压气瓶压力仿真与试验结果对比
Figure 4. Comparison of simulation results and experiment results of pressurized gas-bottle in pumping-back process
图 5 加注过程贮箱气腔压力仿真与试验结果对比
Figure 5. Comparison of simulation results and experiment results of tank pressure in propellant-refilling process
图 6 加注过程充填量仿真与试验结果比对
Figure 6. Comparison of simulation results and experiment results of propellant refilling quantity in propellant-refilling process
图 7 抽气过程中气瓶和贮箱压力变化曲线
Figure 7. Variation curve of pressure in gas-bottle and tank in pumping-back process
图 8 加注过程中贮箱压力及加注速率的变化曲线
Figure 8. Variation curve of pressure and propellant flowrate in tank in propellant-refilling process
表 1 推进剂补加参数
Table 1. Parameters of propellant refueling
参数 数值 气瓶容积/L 40 膜盒贮箱气腔容积/L 85 膜盒贮箱液腔容积/L 200 抽气前推进剂剩余量（体积）/L 0 抽气前膜盒贮箱压力（气体温度为15 ℃）/MPa 2.0 抽气前气瓶压力（气体温度为15 ℃）/MPa 6.9 抽气前膜盒贮箱气腔温度/℃ 15 贮箱气腔抽气目标压力/MPa 0.3 抽气速率（标准大气压101325 Pa下，
气体温度为20 ℃）/（L/h）400 加注时货船贮箱增压压力/MPa 1.9 贮箱液腔目标加注量（体积）/L 192 N2O4密度/（kg/m3） 1445 
下载: 导出CSV
-
[1] MITCHELL J. On-orbit spacecraft re-fluiding[R]. NASA/N99-17786, 1999. [2] 魏延明,潘海林. 空间机动服务平台在轨补给技术研究[J]. 空间控制技术与应用,2008,34(2): 18-22,43.WEI Yanming,PAN Hailin. Research on on-orbit refueling of maneuverable platform[J]. Aerospace Control and Application,2008,34(2): 18-22,43. (in Chinese) [3] 饶大林,闫指江,王书廷,等. 常规推进剂在轨加注技术研究现状与趋势[J]. 导弹与航天运载技术,2015(5): 50-54.RAO Dalin,YAN Zhijiang,WANG Shuting,et al. Current situation and trend analysis on orbital refueling technology for storable propellants[J]. Missiles and Space Vehicles,2015(5): 50-54. (in Chinese) [4] 李虎林,杨震春,付朝晖. 推进剂在轨自动补加技术研究[J]. 中国航天,2012(12): 36-39.LI Hulin,YANG Zhenchun,FU Zhaohui. Research on automatic propellant replenishment technology in orbit[J]. Aerospace China,2012(12): 36-39. (in Chinese) [5] TEGART J, KIRKLAND Z. On-orbit propellant resupply demonstration-flight results[R]. AIAA 1985-1233, 1985. [6] DOMINICK S, DRISCOLL S. Fluid acquisition and resupply experiment (FARE-I) flight results[R]. AIAA 1993-2424, 1993. [7] DOMINICK S, TEGART J, DRISCOLL S L, et al. Fluid acquisition and resupply experiments on space shuttle flights STS-53 and STS-57[R]. NASA/TP-2011-216465, 2011. [8] CHATO D, MARTIN T. Vented tank resupply experiment-flight test results[R]. AIAA97-2815, 1997. [9] ROTENBERGER S, SOOHOO D, ABRAHAM G. Orbital express fluid transfer demonstration system[C]// Proceedings of SPIE(Society of Photo-Optical Instrumentation Engineers). Orlando, US: Internatinal Society for Optical Engineering, 2008: 695808.1-695808.9. [10] ODA M, INAGAKI T, NISHIDA M. Design and development status of ETS-7, an RVD and space robot experiment satellite[R]. NASA/N95- 23700, 1995. [11] GREGORY T, NEWMAN M. Thermal design considerations of the robotic refueling mission (RRM) [R]. AIAA 87-1764, 1987. [12] DOMINICK S. Space station fluid management logistics[R]. NASA/N93-27799, 1993. [13] 白明生,金勇,雷剑宇,等. 天舟一号货运飞船研制[J]. 载人航天,2019,25(2): 249-255.BAI Mingsheng,JIN Yong,LEI Jianyu,et al. Research and development of Tianzhou-1 cargo spacecraft[J]. Manned Spaceflight,2019,25(2): 249-255. (in Chinese) [14] 江铭伟. 俄罗斯空间站推进剂补加程序分析[J]. 火箭推进,2013,39(4): 8-12.JIANG Mingwei. Analysis of propellant refueling program for Russian space station[J]. Journal of Rocket Propulsion,2013,39(4): 8-12. (in Chinese) [15] SAUTER D, HOCHSTEIN J, FITE L. Computational modeling of cryogenic propellant resupply[R]. AIAA2006-984, 2006. [16] 胡齐,李永,耿永兵,等. 一种板式推进剂管理装置(PMD)性能的数值仿真[J]. 空间控制技术与应用,2010,36(3): 55-58.HU Qi,LI Yong,GENG Yongbing,et al. Numerical simulation for capability of a vane PMD to manage propellant[J]. Aerospace Control and Application,2010,36(3): 55-58. (in Chinese) [17] 李乐. 推进剂微重力加注稳定性仿真分析[J]. 火箭推进,2013,39(4): 41-45.LI Le. Simulation and analysis of propellant refueling stability under low-gravity condition[J]. Journal of Rocket Propulsion,2013,39(4): 41-45. (in Chinese) [18] 廖瑛,龚明方,尹嘉娃,等. 空间补加过程的建模与仿真研究[J]. 系统仿真学报,2010,22(6): 1535-1538.LIAO Ying,GONG Mingfang,YIN Jiawa,et al. Research on modeling and simulation of process of propellant refueling to space stations[J]. Journal of System Simulation,2010,22(6): 1535-1538. (in Chinese) -
点击查看大图
计量
- 文章访问数: 70
- HTML浏览量: 23
- PDF量: 32
- 被引次数: 0