低功率N<sub>2</sub>H<sub>4</sub>电弧加热发动机高空模拟试验系统

张莘艾; 汤海滨; 施陈波; 刘宇

低功率N₂H₄电弧加热发动机高空模拟试验系统

北京航空航天大学宇航学院, 北京 100191

基金项目: 国家自然科学基金资助项目(50826007)

详细信息

作者简介:
张莘艾(1981-),男,上海人,博士生,zhangxinai@sa.buaa.edu.cn.

中图分类号: V 439.2
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- 被引次数: 0
出版历程
- 收稿日期: 2009-06-22
- 网络出版日期: 2010-08-30

High altitude simulation experiment system for low power hydrazine arcjet

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 介绍了用于低功率肼(N₂H₄)电弧加热发动机(Arcjet)的高空模拟试验系统,阐述了该系统中的高空模拟真空系统、推进剂供给系统、电源调理单元(PCU,Power Control Unit)、微推力全弹性测量装置、数据采集系统以及其它配套设施.针对低功率肼电弧加热发动机地面试验的特殊要求,重点介绍了有毒推进剂肼(N₂H₄)的供给、微小流量测量、微小推力测量的方法与原理,并在该套系统上进行了系统功能验证性试验.试验证明,该套系统满足低功率肼电弧加热发动机高空模拟试验要求,为推进肼电弧加热发动机的研究与工程应用提供了保障.
- 肼电弧加热发动机 /
- 微小流量测量 /
- 微小推力测量 /
- 数据采集
Abstract: A high altitude simulation experiment system for low power hydrazine arcjet was presented. The elements in this system including vacuum facility, propellant feed system, power control unit, full elastic micro thrust measurement equipment, data acquisition system etc. were depicted in details. To meet the special demands in low power arcjet high altitude simulation experiment, the working process and principle of the propellant feed system, the full elastic steady weighting method micro flow measurement system and the full elastic micro thrust measurement equipment were emphasized. Tests to validate the system were conducted in this system. The results show that the high altitude simulation experiment is steady, reliable and competent for low power hydrazine arcjet high altitude simulation experiment.
- hydrazine arcjet /
- liquid micro flow measurement /
- micro thrust measurement /
- data acquisition

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参考文献(1)

[1] Cruciani G,Deininger W D.A 300-hour endurance test of an arcjet thruster at 1 kW [R].AIAA 93-1900,1993 [2] Knowles S C,Yano S E.Design,testing and integration of a flight-ready hydrazine arcjet system [R].AIAA 89-2720,1989 [3] Knowles S C,Yano S E,Aadland R S.Qualification and life testing of a flight design hydrazine arcjet system [R].AIAA 90-2576,1990 [4] Deininger W D,Stefano R Di,Parisi G,et al.A review of low power arcjet PCU development and testing [R].AIAA 94-3008,1994 [5] 肖应超,汤海滨,刘宇.肼电弧喷射推力器工作方式可替换性数值研究 [J].北京航空航天大学学报,2004,30(9):831-834 Xiao Yingchao,Tang Haibin,Liu Yu.Numerical study on hydrazine arcjet thruster working exchangeability [J].Journal of Beijing University of Aeronautics and Astronautics,2004,30(9):831-834 (in Chinese) [6] 肖应超,汤海滨,刘宇.集气腔总压对电弧喷射推力器工作过程的影响 [J].北京航空航天大学学报,2005,31(9):1031-1035 Xiao Yingchao,Tang Haibin,Liu Yu.Effect of plenum chamber total pressure on arcjet thruster operation[J].Journal of Beijing University of Aeronautics and Astronautics,2005,31(9):1031-1035 (in Chinese) [7] 陈黎明,赵文华,刘岩松.低功率电弧加热发动机的实验研究 [J].应用基础与工程科学学报,2002,10(2):168-173 Chen Liming,Zhao Wenhua,Liu Yansong.Experimental study on low power arcjet [J].Journal of Basic Science and Engineering,2002,10(2):168-173 (in Chinese) [8] 吴汉基,冯学章,刘文喜,等.电弧加热发动机的实验研究 [J].中国空间科学技术,1997(4):41-48 Wu Hanji,Feng Xuezhang,Liu Wenxi,et al.Experimental study on arcjet thruster [J].Chinese Space Science and Technology,1997(4):41-48 (in Chinese) [9] 汤海滨,刘畅,陈树君,等.电弧加热发动机地面试验( Ⅱ)发动机电特性分析[J].推进技术,2006,27(6):546-549 Tang Haibin,Liu Chang,Chen Shujun,et al.Ground experiment on arcjet thrusters (II) electric characteristic analysis [J].Journal of Propulsion Technology,2006,27(6):546-549 (in Chinese) [10] 汤海滨,刘畅,向民,等.微推力全弹性测量装置 [J].推进技术,2007,28(6):703-706 Tang Haibin,Liu Chang,Xiang Min,et al.Full elastic micro thrust measurement equipment [J].Journal of Propulsion Technology,2007,28(6):703-706 (in Chinese)

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