氙气与多种示漏气体漏率转换关系研究*

doi:10.13385/j.cnki.vacuum.2023.03.11

摘要/Abstract

摘要： 电推进技术是我国航天卫星未来重要的推进系统技术,具有比常规化学推进比冲高、推力小、推进剂利用率高等优点,其中离子推进器主要使用氙气作为推进剂。常规的推进系统密封性测试采用氦气作为示漏气体,检漏结果与实际工质氙气的真实漏率存在换算关系,为了能够准确评估电推进系统的实际泄漏状态和漏率数值,亟需开展相关研究。本文通过搭建多种示漏气体测试系统,验证了氙气原位检漏技术的可行性,并由理论分析和实验研究初步获得氙气与氦气、氪气之间的漏率转换关系,以及转换系数理论上下限数值,为后续电推进的检漏工作提供参考依据。

关键词: 电推进系统, 检漏, 氙气, 转换关系, 漏率

Abstract: The electric propulsion technology is an important propulsion system technology for Chinese satellites in the future. It has the advantages of higher specific impulse, lower thrust and higher propellant utilization compared to the conventional chemical propulsion. The ion thrusters mainly use xenon as propellant. Helium is used as the leakage gas in the conventional sealing test of the propulsion system. There is a conversion relationship between the leakage detection result and the actual leakage rate of the xenon. In order to accurately evaluate the actual leakage state and leakage rate of the electric propulsion system, it is urgent to carry out relevant research. In this paper, the feasibility of xenon in-situ leak detection technology is verified by building a several tracer gases testing system. Through theoretical analysis and experimental research, the leak rate conversion relationship between xenon, helium and krypton, as well as the theoretical upper and lower limits of the conversion coefficient, are preliminarily obtained. It will provide a reference for the leak detection of the electric propulsion system.

Key words: electric propulsion system, leak test, xenon, conversion relationship, leak rate

中图分类号: V19

韩琰, 孙立臣, 王静涛, 刘一欢, 陈文卿, 眭霄翔. 氙气与多种示漏气体漏率转换关系研究^*[J]. 真空, 2023, 60(3): 67-71.

HAN Yan, SUN Li-chen, WANG Jing-tao, LIU Yi-huan, CHEN Wen-qing, SUI Xiao-xiang. Research of the Leak Rate Conversion for Xenon and Tracer Gas[J]. VACUUM, 2023, 60(3): 67-71.

参考文献 20

[1]	吴汉基, 蒋远大, 张志远. 电推进技术的应用与发展趋势[J]. 推进技术, 2003, 24(5): 8.
[2]	GOEBELD M, KATZ I.Fundamentals of electric propulsion-ion and hall thrusters[M]. New York: John Wiley & Sons Inc, 2008.
[3]	MARTINEZ-SANCHEZ M, POLLARD J E.Spacecraft electric propulsion-an overview[J]. Journal of Propulsion and Power, 1998, 14(5): 688-699.
[4]	RAYMAN M, WILLIAMS S N.Design of the first interplanetary solar electric propulsion mission[J]. Journal of Spacecraft and Rockets, 2002, 39(4): 589-595.
[5]	JONES R M.A comparison of potential electric propulsion systems for orbit transfer[J]. Journal of Spacecraft and Rockets, 1984, 21(1): 88-95.
[6]	WILBUR P J, JAHN R G, CURRAN F C.Space electric propulsion plasmas[J]. IEEE Transactions on Plasma Science, 1991, 19(6): 1167-1179.
[7]	ZHAO Y S, SUN L C, YU X F, et al.Supercritical Xe as propellant in satellite electric propulsion system: experimental study on thermal physical properties[C]//IPO Conference Series: Materials Science and Engineering. 7th Annual International Conference on Materials Science and Engineering. Hubei, China: IPO, 2019.
[8]	汪旭东, 李国岫, 陈君, 等. 压电比例阀调节的氙气微推进系统流量特性仿真研究[J]. 推进技术, 2019, 40(12): 2867-2873.
[9]	UNDERWOOD S D, SMITH S L. Paper session II-C-verification of international space station component leak rates by helium accumulation method[EB/OL]. (2003-05-01)[2022-09-01]. https://commons.erau.edu/space-congress-proceedings/proceedings-2003-40th/may-1-2003/19/.
[10]	UNDERWOOD S D, SMITH S L.Verification of international space station component leak rates by helium accumulation method[C]//40th Space Congress 2003 International Space Station Advances, Mission Milestones, Mission Operations. Cape Canaveral, USA, 2003.
[11]	李明蓬. 正压氦检漏的几个技术问题[J].导弹与航天运载技术, 1993(4): 66-70.
[12]	BILARDO V J, Jr, VAN DUSEN W. Development of an operational helium leak detection system for the national space transportation system[J]. Materials Evaluation, 1989, 47: 028283.
[13]	SHI J J, SUN L C, ZHAO J C, et al.Charging-vacuum helium mass spectrometer leak detection technology in the application of space products leak testing and error control[C]//International Conference on Mechanics and Fluid Engineering. Amsterdam, Netherlands: World Academy of Science, Engineering and Technology, 2017.
[14]	MARCHAND L, DERENNE M, MASI V.Predicting gasket leak rates using a laminar-molecular flow model[C]//Proceedings of the ASME 2005 Pressure Vessels and Piping Conference. Denver, USA: ASME, 2005.
[15]	黄理胜, 于炳琪. 常见混合气体的四极质谱定量分析方法及有效性评估[J]. 真空, 1997(5): 9-14.
[16]	沈青. 稀薄气体动力学[M]. 北京: 国防工业出版社, 2003.
[17]	王欲知, 陈旭. 真空技术[M]. 2版. 北京: 北京航空航天大学出版社, 2007.
[18]	达道安. 真空设计手册[M]. 3版. 北京: 国防工业出版社, 2004.
[19]	张建军, 张涤新, 赵澜, 等. 不同压力下正压漏孔漏率研究[J]. 真空与低温, 2003, 9(1): 39-42.
[20]	喻新发, 孙立臣, 窦仁超, 等. 电推进系统工质氙气充装特性试验研究[J]. 航天器环境工程, 2014(6): 640-645.

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