40cm离子推力器功率宽范围工作实验研究 *

推进技术 ›› 2018, Vol. 39 ›› Issue (4): 942-947.

40cm离子推力器功率宽范围工作实验研究 *

赵以德,张天平,黄永杰,孙小菁,孙运奎,李娟,杨福全,池秀芬

兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000,兰州空间技术物理研究所真空技术与物理重点实验室，甘肃兰州 730000

发布日期:2021-08-15
作者简介:赵以德，男，博士生，高级工程师，研究领域为离子电推进技术与工程应用。

Experimental Study of 40cm Ion Thruster over a Wide Range of Input Power

Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China,Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China and Science and Technology on Vacuum Technology and Physics Laboratory，Lanzhou Institute of Physics， Lanzhou 730000，China

Published:2021-08-15

摘要/Abstract

摘要： 深空探测任务要求太阳能电推进系统具有大推力、高比冲特性，同时随着航天器离开太阳距离的增加，太阳能效率快速降低，要求电推进系统具备功率宽范围高效工作能力。为了研究兰州空间技术物理研究所研制的40cm离子推力器功率宽范围工作能力，从实验角度研究了1～10kW 40cm离子推力器的工作性能及其变化规律。通过对离子推力器工作参数和性能的分析与计算，依据功率调节方法确定了40cm离子推力器1～10kW多模式工作点电参数；通过阴极流率优化和放电损耗优化实验确定了多模式工作点最佳供气参数。在设计确定的电参数和实验确定的供气参数下，开展了1～10kW调节实验，获取了40cm离子推力器的工作性能及其变化规律。实验结果表明:40cm离子推力器可在1～10kW内稳定工作，推力42～336mN，比冲2174～4389s，效率41%～72%；随功率增加效率增高，当功率大于2.5kW时效率大于63%。

关键词: 离子推力器；功率宽范围调节；高效率；深空探测

Abstract: It is necessary that the Solar Electric Propulsion systems provide high thrust and high specific impulse for primary propulsion in deep space exploration missions. While the electric thruster must be capable of deep power throttling since the power available from the solar panel arrays reduces as the spacecraft distance from the sun increases. In order to study the operating performance of 40cm ion thruster over a wide range of input power， which has been developed by Lanzhou Institute of Physics， the operating parameters of 40cm ion thruster were evaluated experimentally at various input power levels. Operational electric parameters of 40cm ion thruster at various input power levels were selected by analyzing and calculating its parameters and performance with theory assumptions and throttling technique. The optimal flow rates at various beam currents?were determined through discharge performance tests at various cathode flow rates and discharge propellant utilization efficiencies. Based on these results the performance of 40cm ion thruster was evaluated at each input power throttling point range 1～10kW. The results showed that the 40cm ion thrust can operate steadily over an input power envelope of 1～10kW， thrust range 42～336mN， specific impulse varies 2174～4389s， and efficiency range 0.41～0.72. The efficiency increases with increasing input power and is higher than 0.63 as the input power is greater than 2.5kW.

Key words: Ion thruster；Wide power throttling range；High efficiency；Deep space exploration

赵以德,张天平,黄永杰,孙小菁,孙运奎,李娟,杨福全,池秀芬. 40cm离子推力器功率宽范围工作实验研究 *[J]. 推进技术, 2018, 39(4): 942-947.

ZHAO Yi-de,ZHANG Tian-ping,HUANG Yong-jie,SUN Xiao-jing,SUN Yun-kui,LI Juan,YANG Fu-quan,CHI Xiu-fen. Experimental Study of 40cm Ion Thruster over a Wide Range of Input Power[J]. Journal of Propulsion Technology, 2018, 39(4): 942-947.

参考文献

[1] Rawlin V K, Sovey J S, John H A. An Ion Propulsion System for NASA′s Deep Space Missions[R]. A1AA 99-4612.
[2] Brophy J R, Mareucei M G, Ganapathi C B, et al. The Ion Propulsion System for Dawn[R]. AIAA 2003-4542.
[3] Oleson S, Gefert L, Benson S, et al. Mission Advantages of NEXT: NASA′s Evolutionary Xenon Thruster[R]. AIAA 2002-3969.
[4] Shastry R D, Herman A, Soulas G C, et al. Status of NASA′s Evolutionary Xenon Thruster (NEXT) Long-Duration Test as of 50000h and 900kg Throughput[R]. IEPC-2013-121.
[5] Hitoshi K, Yukio S, Tetsuya Y, et al. Report during Two Years on HAYABUSA Explorer Propelled by Microwave Discharge Ion Engines[R]. AIAA 2005-3673.
[6] Tighe W G, Chien K R, Solis E, et a1. Performance Evaluation of the XIPS-25cm Thruster for Application to NASA Discovery Missions[R] . AIAA 2006-4666.
[7] Rawlin V K. Power Throttling the NSTAR Ion Thruster[R]. AIAA 95-2515.
[8] Herman D A, Soulas G C, Patterson M J. Performance Evaluation of the Prototype Model NEXT Ion Thruster[R]. AIAA 2007-5212.
[9] Patterson M J. NEXT Study of Thruster Extended-Performance[R]. AIAA 2006-4664.
[10] Goebel D M, Martinez-Lavin M and Bond T A. Performance of XIPS Electric Propulsion in on-Orbit Station Keeping of the Boeing 702 Spacecraft[R]. AIAA 2002-4348.
[11] 杨福全, 江豪成, 张天平, 等. 20cm离子推力器飞行试验工作性能评价[J]. 推进技术, 2016, 37(4): 783-787. (YANG Fu-quan, JIANG Hao-cheng, ZHANG Tian-ping, et al. Flight Test Performance Evaluation of 20cm Ion Thruster[J]. Journal of Propulsion Technology, 2016, 37(4): 783-787.)
[12] 郑茂繁, 江豪成. 改善离子推力器束流均匀性的方法[J]. 推进技术, 2011, 32(6): 762-765. (ZHENG Mao-fan, JIANG Hao-cheng. Method of Improving Beam Current Profile for Ion Thruster[J]. Journal of Propulsion Technology, 2011, 32(6): 762-765.)
[13] Zhang T P. Initial Flight Test Results of the LIPS-200 Electric Propulsion System on SJ-9A Satellite[R]. IEPC-2013-47.
[14] Zhang T P. The LIPS-200 Ion Electric Propulsion System Development for the DFH-3B Satellite Platform[R]. IAC-13-C4.4, 2013.
[15] 郑茂繁, 张天平, 孟伟, 等. 20cm氙离子推力器性能扩展研究[J]. 推进技术, 2015, 36(7): 1116-1120. (ZHENG Mao-fan, ZHANG Tian-ping, MENG Wei, et al. Research of Improvement Performance for 20cm Xenon Ion Thruster[J]. Journal of Propulsion Technology, 2015, 36(7): 1116-1120.)
[16] Goebel D M, Katz I. Fundamentals of Electric Propulsion: Ion and Hall Thruster[M]. California: JPL Space Science and Technology Series, 2008: 24-28.(编辑:田佳莹)　　　　　　　　　　　　　*　收稿日期:2017-02-28；修订日期:2017-05-05。作者简介:赵以德,男,博士生,高级工程师,研究领域为离子电推进技术与工程应用。E-mail: zh_yide@sina.com