Direct thrust test and asymmetric performance of porous ionic liquid electrospray thruster

doi:10.1016/j.cja.2022.09.007

IMECH-IR > 微重力重点实验室

	Direct thrust test and asymmetric performance of porous ionic liquid electrospray thruster
	Guo, Yuntao ; Sun, Wei ; Sun, Zhenning ; Wu, Zhiwen ; He JW(贺建武); Yang C(杨超); Wang, Ningfei
发表期刊	CHINESE JOURNAL OF AERONAUTICS
	2023-04
卷号	36 期号:4 页码:120-133
ISSN	1000-9361
摘要	In order to meet the demand of CubeSats for low power and high-performance micro -propulsion system, a porous ionic liquid electrospray thruster prototype is developed in this study. 10 x 10 conical emitter arrays are fabricated on an area of 3.24 cm2 by computer numerical control machining technology. The propellant is 1-ethyl-3-methylimidazolium tetrafluoroborate. The over-all dimension of the assembled prototype is 3 cm x 3 cm x 1 cm, with a total weight of about 15 g (with propellant). The performance of this prototype is tested under vacuum. The results show that it can work in the voltage range of +/- 2.0 kV to +/- 3.0 kV, and the maximum emission current and input power are about 355 lA and 1.12 W. Time of Flight (TOF) mass spectrometry results show that cationic monomers and dimers dominate the beam in positive mode, while a higher proportion of higher-order solvated ion clusters in negative mode. The maximum specific impulse is 2992 s in positive mode and 849 s in negative mode. The thrust is measured in two methods: one is calculated by TOF results and the other is directly measured by high-precision torsional thrust stand. The thrust (T) obtained by these two methods conforms to a certain scaling law with respect to the emis-sion current (Iem) and the applied voltage (Vapp), following the scale of T ti IemVapp 0.5 , and the thrust range is from 2.1 lN to 42.6 lN. Many thruster performance parameters are significantly different in positive and negative modes. We speculate that due to the higher solvation energy of the anion, more solvated ion clusters are formed rather than pure ions under the same electric field. It may help to improve thruster performance if porous materials with smaller pore sizes are used as reservoirs. Although there are still many problems, most of the performance parameters of ILET-3 are good, which can theoretically meet the requirements of CubeSats for micro-propulsion system.(c) 2022 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
关键词	Asymmetric performance Direct thrust test Ionic liquid electrospray thruster Time of flight mass spec-trometry Torsional thrust stand
DOI	10.1016/j.cja.2022.09.007
收录类别	SCI ; EI ; CSCD
语种	英语
WOS记录号	WOS:000986689500001
项目资助者	National Key R&D Program of China [2020YFC2201103]
论文分区	一类
力学所作者排名	1
RpAuthor	Wu, ZW
引用统计	被引频次：20[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/92253
专题	微重力重点实验室
作者单位	1.(Guo Yuntao, Sun Wei, Wu Zhiwen, Wang Ningfei) Beijing Inst Technol Sch Aerosp Engn Beijing 100081 Peoples R China 2.(Sun Zhenning) Beijing Inst Elect Syst Engn Beijing 100039 Peoples R China 3.(He Jianwu, Yang Chao) Chinese Acad Sci Inst Mech Key Lab Micrograv Beijing 100190 Peoples R China 4.(He Jianwu, Yang Chao) Univ Chinese Acad Sci Sch Engn Sci Beijing 100049 Peoples R China
推荐引用方式 GB/T 7714	Guo, Yuntao,Sun, Wei,Sun, Zhenning,et al. Direct thrust test and asymmetric performance of porous ionic liquid electrospray thruster[J]. CHINESE JOURNAL OF AERONAUTICS,2023,36,4,:120-133.Rp_Au:Wu, ZW
APA	Guo, Yuntao.,Sun, Wei.,Sun, Zhenning.,Wu, Zhiwen.,贺建武.,...&Wang, Ningfei.(2023).Direct thrust test and asymmetric performance of porous ionic liquid electrospray thruster.CHINESE JOURNAL OF AERONAUTICS,36(4),120-133.
MLA	Guo, Yuntao,et al."Direct thrust test and asymmetric performance of porous ionic liquid electrospray thruster".CHINESE JOURNAL OF AERONAUTICS 36.4(2023):120-133.

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