Influence of acceleration grid voltage and anode flow rate on performance of ion thruster

Li Jian-Peng; Jin Wu-Yin; Zhao Yi-De

doi:10.7498/aps.71.20211316

Abstract

In order to achieve the optimal performance and reliability of the ion thruster in a wide power range, the influence of acceleration grid voltage and anode flow rate on the performance of ion thruster are studied experimentally and theoretically. The results show that in a certain range the ion beam current decreases continuously with the decrease of the absolute value of the accelerating voltage, and then increases suddenly. The electron backstreaming limited voltages in large and small thrust modes are –140 and –115 V, respectively. When the anode flow rate increases, the discharge voltage and discharge loss increase monotonically, and the deceleration current decreases monotonously. Under the power of 300−4850 W, the thrust is 11−188 mN, the specific impulse is 1800−3567 s, and the efficiency ranges from 34% to 67% by adjusting the anode current, grid voltage and working fluid gas flow. The maximum efficiency of thruster reaches 67% at 3000 W. This turning point is critical for thruster design and on-orbit applications. Choosing a reasonable range of working parameters can improve the performance and life of the thruster in application.

Keywords:

Authors and contacts

1.
School of Mechanical and Electronical Engineering, Lanzhou University of Technology, Lanzhou 730050, China
2.
Science and Technology on Vacuum Technology and Physics Laboratory, Lanzhou Institute of Physics, Lanzhou 730000, China

Corresponding author: Li Jian-Peng, ljplzjtedu@163.com

Funds: Project supported by the National Natural Science Foundation of China (Grant No. 61601210) and the Fund for Distinguished Young Scholars of China Academy of Space Technology.

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References

[1]	Hutchins M, Simpson H, Palencia Jiménez J 2015 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric Propulsion Conference and 6th Nanosatellite Symposium Hyogo-Kobe, Japan, July 4−10, 2015 p2015-b-1311
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[24]	赵以德, 张天平, 黄永杰, 孙小菁, 孙运奎, 李娟, 杨福全, 池秀芬 2018 推进技术 39 942 Zhao Y D, Zhang T P, Huang Y J, Sun X J, Sun Y K, Li J, Yang F Q, Chi X F 2018 J. Propul. Technol. 39 942
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Cited By

图 1 离子推力器试验组成图

Figure 1. Schematic of experiental principle.

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图 2 离子推力器点火照片

Figure 2. Discharge of the ion thruster.

DownLoad: Full-Size Img PowerPoint

图 3 离子束电流随加速电压变化情况　(a) 小推力模式; (b) 大推力模式

Figure 3. Beam current as a function of accel-grid voltage for different thrust mode: (a) Low thrust mode; (b) high thrust mode.

DownLoad: Full-Size Img PowerPoint

图 4 放电电压随阳极流率的变化情况　(a) 小推力模式; (b) 大推力模式

Figure 4. Discharge voltage as a function of anode mass flow rate for different thrust mode: (a) Low thrust mode; (b) high thrust mode.

DownLoad: Full-Size Img PowerPoint

图 5 放电损耗随阳极流率的变化情况　(a) 小推力模式; (b) 大推力模式

Figure 5. Discharge loss as a function of anode mass flow rate for different thrust mode: (a) Low thrust mode; (b) high thrust mode.

DownLoad: Full-Size Img PowerPoint

图 6 减速电流随阳极流率的变化情况　(a) 小推力模式; (b) 大推力模式

Figure 6. Decel-current as a function of anode mass flow rate for different thrust mode: (a) Low thrust mode; (b) high thrust mode.

DownLoad: Full-Size Img PowerPoint

图 7 推力、比冲和效率随功率变化曲线　(a) 推力; (b) 比冲; (c) 效率

Figure 7. Thrust, specific impulse and efficiency as a function of input power: (a) Thrust; (b) specific impulse; (c) efficiency.

DownLoad: Full-Size Img PowerPoint

表 1 多模式离子推力器应用情况

Table 1. Application of multi-mode ion thruster.

离子推力器	推力器性能指标
离子推力器	推力/mN	比冲/s	效率	功率/kW
NSTAR^[7-10]	19.5—92	1951—3083	38%~59%	0.5—2.3
NEXT^[11]	25.5—236	1400—4190	32%~71%	0.5—6.9
XIPS-25^[12]	14.4—173.7	1610—3664	35%~66%	0.3—4.5
IT-500^[13]	375, 585, 750	7142	—	18, 28, 35
T6^[14]	76.5, 102.1127.7, 147.8	3720, 38803990, 3980	—	2520, 32804040, 4620

DownLoad: CSV

[1]	Hutchins M, Simpson H, Palencia Jiménez J 2015 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric Propulsion Conference and 6th Nanosatellite Symposium Hyogo-Kobe, Japan, July 4−10, 2015 p2015-b-1311
[2]	Burak K K, Deborah A L 2017 J. Propul. Power 33 264 Google Scholar
[3]	Li J X, Wang Z H, Zhang Y B, Fu H M, Liu C R, Krishnaswamy S 2016 J. Propul. Power 32 948 Google Scholar
[4]	Williams L T, Walker M L R 2014 J. Propul. Power 30 645 Google Scholar
[5]	Canuto E, Massotti L 2009 Acta Astronaut. 64 325 Google Scholar
[6]	Groh K H, Loeb H W 1994 Rev. Sci. Instrum. 65 1741 Google Scholar
[7]	Rawlin V K, Sovey J S, Hamley J A 1999 Presented at the 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit Albuquerque, USA, September 28−30, 1999 p99- 4612-1
[8]	Brophy J R, Mareucei M G, Ganapathi C B, Garner C E, Henry M D, Nakazono B, Noon D 2003 Presented at the 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit Huntsville, USA, July 20−23, 2003 p2003-4542-1
[9]	Rayman M D, Varghese P, Lehman D H, Livesay L 2000 Acta Astronaut. 47 475 Google Scholar
[10]	Garner C E, Rayman M D, Brophy J R, Mikes S C 2011 Presented at the 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit San Diego, USA, July 31−August 03, 2011 p2011-5661-1
[11]	Malone S P, Soulas G C 2004 Presented at the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit Fort Lauderdale, USA, July 11−14, 2004 p2004-3784-1
[12]	Goebel D M, Martinez-Lavin M, Bond T A, King M 2002 Presented at the 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Joint Propulsion Conferences Indianapolis, USA, July 7−10, 2002 p2002-4348-1
[13]	Koroteev A S, Lovtsov A S, Muravlev V A 2017 Eur. Phys. J. D 71 120
[14]	Snyder J S, Goebel D M, Hofer R R, Polk J E 2012 J. Propul. Power. 28 371 Google Scholar
[15]	Herman D A, Soulas G C, Patterson M J 2007 Presented at the 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit Cincinnati, USA, July 8−11, 2007 p2007-5212-1
[16]	Brophy J R, Katz I, Polk J E, Anderson J R 2002 Presentedat the 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit Indianapolis, USA, July 7−10, 2002 p2002-4261-1
[17]	Wang J, Polk J, Brophy J, Katz I 2003 J. Propul. Power 19 1192 Google Scholar
[18]	陈茂林, 夏广庆, 毛根旺 2014 物理学报 63 182901 Google Scholar Chen M L, Xia G Q, Mao G W 2014 Acta Phys. Sin. 63 182901 Google Scholar
[19]	龙建飞, 张天平, 李娟, 贾艳辉 2017 物理学报 66 162901 Google Scholar Long J F, Zhang T P, Li J, Jia Y H 2017 Acta Phys. Sin. 66 162901 Google Scholar
[20]	赵以德, 李娟, 吴宗海, 黄永杰, 李建鹏, 张天平 2020 物理学报 69 115203 Google Scholar Zhao Y D, Li J, Wu Z H, Huang Y J, Li J P, Zhang T P 2020 Acta Phys. Sin. 69 115203 Google Scholar
[21]	Wirz R, Goebel D M 2008 Plasma Sources Sci. Technol. 17 035010 Google Scholar
[22]	王雨玮, 任军学, 吉林桔, 汤海滨 2016 中国空间科学技术 36 77 Google Scholar Wang Y W, Ren J X, Ji L J, Tang H B 2016 Chin. Space Sci. Technol. 36 77 Google Scholar
[23]	李建鹏, 张天平, 赵以德, 李娟, 郭德洲, 胡竟 2021 推进技术 42 1435 Li J P, Zhang T P, Zhao Y D, Li J, Guo D Z, Hu J 2021 J. Propul. Technol. 42 1435
[24]	赵以德, 张天平, 黄永杰, 孙小菁, 孙运奎, 李娟, 杨福全, 池秀芬 2018 推进技术 39 942 Zhao Y D, Zhang T P, Huang Y J, Sun X J, Sun Y K, Li J, Yang F Q, Chi X F 2018 J. Propul. Technol. 39 942
[25]	Zhang T P, Wang X Y, Jiang H C 2013 Presented at the 33th International Electric Propulsion Conference Washington, USA, October 6−10, 2013 p2013-48-1
[26]	Jahn R G, Von J W 2006 Physics of Electric Propulsion (New York: Dover Pubns) p68
[27]	Farnell C C, Williams J D 2011 Plasma Sources Sci. Technol. 20 025006 Google Scholar
[28]	Bittencourt J A 1980 Fundamentals of Plasma Physics (New York: Springer) p95
[29]	Piel A, Brown M 2011 Phys. Today 64 55
[30]	Goebel D M, Katz I 2008 Fundamentals of Electric Propulsion: Ion and Hall Thruster (Hoboken: John Wiley and Sons) p245
[31]	Green T S 1976 J. Phy. D:Appl. Phys. 9 1165 Google Scholar
[32]	Goebel D M, Jameson K K, Katz I 2007 Phys. Plasmas 14 103508 Google Scholar
[33]	Palluel P, Shroff A M 1980 J. Appl. Phys. 51 2894 Google Scholar

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