低功率电弧加热推力器喷管温度与性能

推进技术 ›› 2011, Vol. 32 ›› Issue (6): 852-856.

低功率电弧加热推力器喷管温度与性能

潘文霞,黄河激,孟显,吴承康

中国科学院力学研究所,北京 100190;中国科学院力学研究所,北京 100190;中国科学院力学研究所,北京 100190;中国科学院力学研究所,北京 100190

发布日期:2021-08-15
作者简介:潘文霞(1957—),女,博士,研究员,研究领域为应用等离子体力学。E-mail:wxpan@imech.ac.cn
基金资助:
国家自然科学基金(7,4, 10921062)。

Effects of nozzle temperature on performance of low power arcjet thrusters

Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190,China;Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190,China;Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190,China;Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190,China

Published:2021-08-15

摘要/Abstract

摘要： 电弧加热推力器利用直流电弧放电加热推进剂,并将加热后的推进剂通过拉瓦尔喷管高速喷出产生推力。电弧加热推力器的性能与其喷管内部复杂的传热与流动以及能量转换过程密切相关。分别以纯氩、氮、氢气以及氢/氮混合气为电弧加热推力器的推进剂,在推进剂供给流量4~270mg/s,弧电流4~12A,环境压力低于20Pa的条件下,实时检测了自然辐射冷却及推进剂再生冷却喷管的电弧加热推力器在运行过程中的喷管外表面温度、弧电压、产生的推力等参数及其变化,综合分析了喷管温度变化对推力器性能的影响。

关键词: 电弧加热推力器;喷管温升;电弧特性;性能变化

Abstract: DC discharge in arcject thruster is used to heat up the injected propellant, which is then accelerated and ejected from a de Laval nozzle at high speed to create thrust. The performance of the arcjet thruster is affected by the complex flow and heat transfer process in its nozzle to a large extent. Performance of arcjet thrusters with radiation or regenerative cooled nozzle was compared in a wide range of operating parameters. Argon, nitrogen, hydrogen and hydrogen-nitrogen mixture were used as the propellants with the feeding rate of 4~270 mg/s. The arc current was set to be 4~12A and the experimental chamber pressure was below 20Pa. Evolutions of nozzle temperature, arc voltage and the generated thrust were measured and the dependence of arcjet performance on the nozzle temperature was discussed.

Key words: Arcjet thruster; Nozzle temperature; Discharge behavior; Thruster performance

潘文霞,黄河激,孟显,吴承康. 低功率电弧加热推力器喷管温度与性能[J]. 推进技术, 2011, 32(6): 852-856.

参考文献

[2] John Slough, Ewing J J.Microarcjet microthruster for nanosat applications[R].AIAA 2007-5181.
[3] Fife J M, Bromaghim D R, Chart D A, et al.Orbital performance measurements of air force electric propulsion space experiment ammonia arcjet[J].J.Propulsion and Power, 2,8(4):749-753.
[4] Sackheim R L.Overview of United States space propulsion technology and associated space transportation systems[J].J.Propulsion and Power, 6,2(6):1310-1333.
[5] Lichtin D A.An overview of electric propulsion activities in US industry-2005[R].AIAA 2005-3532.
[6] 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,1997,17(4):41-48.
[7] 吴汉基,冯学章,蒋远大,等.氢氮混合气电弧加热发动机的性能试验[J].中国空间科学技术,2002,22(4):57-63.
[8] 刘宇,张振鹏,吴汉基,等.电弧等离子体发动机初步研究[J].北京航空航天大学学报,1998,24(3):365-368.
[9] 肖应超,汤海滨.电弧喷射推力器化学非平衡数值模拟[J].推进技术,2004,25(5):458-462.(XIAO Ying-chao,TANG Hai-bin.Chemical non-equilibrium simulation on arcjet thrusters[J].Journal of Propulsion Technology,4,5(5):458-462.)
[10] 廖宏图,吴铭岚,汪南豪.超声速电弧喷射器内等离子体流场的数值模拟[J].推进技术,1999,20(6):52-57.(LIAO Hong-tu,WU Ming-lan,WANG Nan-hao.Numerical simulation on the internal plasma flow of a supersonic arcjet [J].Journal of Propulsion Technology,9,0(6):52-57.)
[11] 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.
[12] 沈岩,赵文华,石泳,等.发射光谱测量电弧加热发动机羽流温度[J].推进技术,2005,26(1):72-75.(SHEN Yan,ZHAO Wen-hua,SHI Yong,et al.Temperature measurement of arcjet plume with emission spectrum[J].Journal of Propulsion Technology,5,6(1):72-75.)
[13] Wenxia Pan, Teng Li, Chengkang Wu.Effects of anode temperature on working characteristics and performance of a low power arcjet thruster[J].Chinese Physics Letters, 9,6(12).
[14] Pan W X, Meng X, Huang H J, et al.Plume parameters and thruster properties of a low power arcjet[C]. Hongkong and Macao:The 2nd International Symposium on Computational Mechanics, ISCM 2-5,9.
[15] 李腾,潘文霞,林烈,等.一种电弧加热推进器推力测试架[J].宇航计测技术,8,8(2):17-20.
[16] Chengkang Wu, Haixin Wang, Xian Meng, et al.Aerodynamics of indirect thrust measurement by the impulse method[J].Acta Mechanica Sinica, 1,7(2):152-163.
[17] Heji Huang, Wenxia Pan, Xian Meng, et al.Development of arc root attachment in the nozzle of 1 kW N₂ and H₂-N₂ arcjet thrusters[C].Bochum:International Symposium on Plasma Chemistry,2009.