Research progress of ionic liquid micropropulsion technology

被引：0
|
作者：
Fan Y. [1 ]
Xia G. [1 ,2 ]
Han Y. [1 ]
Lu C. [1 ,2 ]
Sun B. [1 ,2 ]
Ding L. [3 ]
机构：
[1] State Key Laboratory of Structural Analysis for Industrial Equipment, Dalian University of Technology, Dalian, 116024, Liaoning
[2] Key Laboratory of Advanced Technology for Aerospace Vehicles, Liaoning Province, Dalian University of Technology, Dalian, 116024, Liaoning
[3] Beijing Institute of Spacecraft Environment Engineering, China Academy of Space Technology, China Aerospace Science and Technology Corporation, Beijing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2020年 / 35卷 / 06期
关键词：
Electric propulsion; Emission condition; Ionic liquid; Micropropulsion; Thruster efficiency;
D O I：
10.13224/j.cnki.jasp.2020.06.018
中图分类号：
学科分类号：
摘要：
The basic structure and working principle of ionic liquid thrusters, including the restrictions on particle emission and the commonly used operating regimes, were introduced. The common classification methods of ionic liquid thruster were summarized. The presently wide-used experimental or simulation methods, and the related progress on emission threshold field strength, beam divergence, polydispersive efficiency, long-term working stability and other issues were reviewed to compare and analyze the working conditions suitable for particle emission and more accurate simulation methods. The future research ideas and reference for the improved design, operating regime setting, and performance evaluation of ionic liquid thruster were also presented. Results show that increasing the flow resistance of propellant and array density of emitter is the appropriate means to improve the efficiency and thrust of the ionic liquid thruster, and changing the emitter voltage polarity and increasing the emitter voltage gradually by using the closed-loop control method is the effective way to maintain the thrust and improve the working stability of the thruster. © 2020, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：1275 / 1285
页数：10
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  • [1] HAN Quandong, HONG Xin, ZHOU Haiqing, Analysis on requirement and development of space propulsion technology, Journal of Rocket Propulsion, 38, 2, pp. 9-15, (2012)
  • [2] SELVA D, KREJCI D., A survey and assessment of the capabilities of Cubesats for Earth observation, Acta Astronautica, 74, pp. 50-68, (2012)
  • [3] LEVCHENKO I, BAZAKA K, DING Y, Et al., Space micropropulsion systems for Cubesats and small satellites: From proximate targets to furthermost frontiers, Applied Physics Reviews, 5, (2018)
  • [4] LOZANO P C, WARDLE B L, MOLONEY P, Et al., Nanoengineered thrusters for the next giant leap in space exploration, MRS(Materials Research Society) Bulletin, 40, 10, pp. 842-849, (2015)
  • [5] LI Yong, LIU Xuhui, WANG Xudong, Et al., Review and prospect on the large-range thrust throttling technology with extremely small thrust, Aerospace Control and Application, 45, 6, pp. 1-12, (2019)
  • [6] HU Yiming, MEI Jianwei, LUO Jun, TianQin project and international collaboration, Chinese Science Bulletin, 64, 24, pp. 2475-2483, (2019)
  • [7] COURTNEY D G, SHEA H, DANNENMAYER K, Et al., Charge neutralization and direct thrust measurements from bipolar pairs of ionic electrospray thrusters, Journal of Spacecraft and Rockets, 55, 1, pp. 54-65, (2017)
  • [8] INOUE N, NAGAO M, MURAKAMI K, Et al., Fabrication of a high-density emitter array for electrospray thrusters using field emitter array process, Japanese Journal of Applied Physics, 58, SE, pp. 1-7, (2019)
  • [9] COURTNEY D G, DANDAVINO S, SHEA H., Comparing direct and indirect thrust measurements from passively fed ionic electrospray thrusters, Journal of Propulsion and Power, 32, 2, pp. 392-407, (2016)
  • [10] HENNING T, HUHN K, ISBERNER L W, Et al., Miniaturized electrospray thrusters, IEEE Transactions on Plasma Science, 46, 2, pp. 214-218, (2018)
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