Development and Experimental Characteristics of Indium Needle-Type Field Emission Electric Propulsion Thruster

Journal of Propulsion Technology ›› 2018, Vol. 39 ›› Issue (4): 955-960.

• Electric Propulsion and Other Advanced Propulsion • Previous Articles

Development and Experimental Characteristics of Indium Needle-Type Field Emission Electric Propulsion Thruster

School of Mechanical Engineering，Shanghai Jiaotong University，Shanghai 200240，China,School of Mechanical Engineering，Shanghai Jiaotong University，Shanghai 200240，China,School of Mechanical Engineering，Shanghai Jiaotong University，Shanghai 200240，China,Shanghai Institute of Space Propulsion，Shanghai 201112，China,School of Mechanical Engineering，Shanghai Jiaotong University，Shanghai 200240，China,Shanghai Institute of Space Propulsion，Shanghai 201112，China,Shanghai Institute of Space Propulsion，Shanghai 201112，China and Shanghai Institute of Space Propulsion，Shanghai 201112，China

Published:2021-08-15

针式铟场发射电推力器的研制及实验特性 *

郭登帅¹,康小明¹,刘欣宇¹,杭观荣²,贺伟国¹,余水淋²,薛伟华²,李彦达²

上海交通大学机械与动力工程学院，上海 200240,上海交通大学机械与动力工程学院，上海 200240,上海交通大学机械与动力工程学院，上海 200240,上海空间推进研究所，上海 201112,上海交通大学机械与动力工程学院，上海 200240,上海空间推进研究所，上海 201112,上海空间推进研究所，上海 201112,上海空间推进研究所，上海 201112

作者简介:郭登帅，男，博士生，研究领域为场发射电推进技术与理论。
基金资助:
国家自然科学基金(51675341)；中国科学院微小卫星重点实验室开放课题(KFKT13SYS4)。

Abstract

Abstract: To develop an indium needle-type FEEP thruster， the needle tip of the FEEP thruster was fabricated by electrochemical etching and was roughened to facilitate the flow of the propellant indium. The needle was wetted under vacuum condition. The developed experimental prototype of In-FEEP was ignited successfully. The characteristics of the thruster including I-V curves of tips with different radii and its thrust were obtained. The experimental results showed that the threshold voltage is dependent on the tip radius that the smaller the tip radius， the lower the threshold voltage is. The experimental prototype could provide continuous thrust output which is 30μN at maximum.

Key words: FEEP；Needle；Roughening；Wetting

摘要： 为了研制针式铟场发射电推力器实验样机，采用微细电化学腐蚀法制备了场发射电推力器的核心部件发射针，并对发射针进行了表面粗化以促进推进剂的输运，研究了真空环境中发射针的浸润方法，实现了推力器的点火，并测得了不同针尖尺寸的发射针的I-V特性曲线和推力值。实验结果表明，发射针针尖半径决定了点火起始电压的大小，针尖半径越小，点火起始电压越低；推力器样机有连续的推力输出，最大推力可达30μN。

关键词: 场发射电推力器；发射针；粗化；浸润

GUO Deng-shuai¹,KANG Xiao-ming¹,LIU Xin-yu¹,HANG Guan-rong²,HE Wei-guo¹,YU Shui-lin²,XUE Wei-hua²,LI Yan-da². Development and Experimental Characteristics of Indium Needle-Type Field Emission Electric Propulsion Thruster[J]. Journal of Propulsion Technology, 2018, 39(4): 955-960.

郭登帅,康小明,刘欣宇,杭观荣,贺伟国,余水淋,薛伟华,李彦达. 针式铟场发射电推力器的研制及实验特性 *[J]. 推进技术, 2018, 39(4): 955-960.

References

[1] 石荣, 李潇, 邓科. 微纳卫星发展现状及在光学成像侦察中的应用[J]. 航天电子对抗, 2016, 32(1): 8-13.
[2] 毛根旺, 韩先伟, 杨涓, 等. 电推进研究的技术状态和发展前景[J]. 推进技术, 2000, 21(5): 1-5. (MAO Gen-wang, HAN Xian-wei, YANG Juan, et al. Research State of Electric Propulsion and Its Development Prospect[J]. Journal of Propulsion Technology, 2000, 21(5): 1-5.)
[3] 张郁. 电推进技术的研究应用现状及其发展趋势[J]. 火箭推进, 2005, 31(2): 27-36.
[4] 吴汉基, 蒋远大, 张志远. 电推进技术的应用与发展趋势[J]. 推进技术, 2003, 24(5): 385-392. (WU Han-ji, JIANG Yuan-da, ZHANG Zhi-yuan. Application and Development Trend of Electric Propulsion Technology[J]. Journal of Propulsion Technology, 2003, 24(5): 385-392.)
[5] Floyd A. Conceptual Design of an Orbiting Dragfree International Explorer (ODIE) Small Satellite Mission[C].Utah: Proceedings of 11th Small Satellite Conference, 1997.
[6] Marcuccio S, Genovese A, Andrenucci M. FEEP Microthruster Technology Status and Potential Applications[C]. Turin: 48th International Astronautical Federation Congress, 1997.
[7] Wielders A A, Calvel B, Swinkels B L, et al. Metrology Concepts for a Space Interferometer Mission: SMART-2[C]. Waikoloa: Proceedings of SPIE, 2003.
[8] Fridlund C V M. Darwin-the Infrared Space Interferometry Mission[J]. ESA Bulletin, 2000, 103(3): 20-25.
[9] Roussel J F ?, Tondu T, Mateo-Velez J C, et al. Modeling of FEEP Plume Effects on MICRO- SCOPE Spacecraft[J]. IEEE Transactions on Plasma Science, 2008, 36(5): 2378-2386.
[10] Tajmar M, Scharlemann C, Genovese A, et al. Indium FEEP Micropropulsion Subsystem for LISA Pathfinder[R]. AIAA 2006-4826.
[11] Nobili A M, Bramanti D, Polacco E, et al. The “Galileo Galilei”(GG) Project: Testing the Equivalence Principle in Space and on Earth[J]. Advances in Space Research, 2000, 25(6): 1231-1235.
[12] Rüdenauer R G, Steiger W, Arends H, et al. A Liquid Metal Ion Sources for Space Application[J]. Journal de Physique, 1988, 49(C6): 161-166.
[13] Fehringer M, Ruedenauer F, Steiger W. Indium Liquid-Metal Ion Sources as MicroNewton Thrusters[C]. Pasadena: the Second International Laser Interferometer Space Antenna Symposium, 1998.
[14] Tajmar M, Genovese A, Steiger W. Indium Field Emission Electric Propulsion Microthruster Experimental Characterization[J]. Journal of Propulsion Power, 2004, 20(2): 211-218.
[15] Genovese A, Tajmar M, Buldrini N, et al. 2000-Hour Endurance Test of Indium Field Emission Electric Propulsion Microthruster Cluster[J]. Journal of Propulsion and Power, 2004, 20(2): 219-227.
[16] Genovese A, Buldrini N, Andres K, et al. 5000h Endurance Test of an Indium FEEP 2×2 Cluster[R]. AIAA 2006-4826.
[17] Genovese A, Buldrini N, Schnitzer R, et al. 3000 Hour Lifetime Test of an Indium FEEP Cluster for the LISA Pathfinder Mission[R]. IEPC 2007-140.
[18] Vasiljevich I, Tajmar M, Grienauer W, et al. Development of an Indium mN-FEEP Thruster[R]. AIAA 2008-4534.
[19] Reissner A. Lifetime Testing of the mN-FEEP Thruster[R]. AIAA 2016-5045.
[20] Nicolini D, Chesta E, Gonzalez del Amo J, et al. FEEP-5 Thrust Validation in the 10-100 μN Range with a Simple Nulled-Pendulum Thrust Stand: Integration Procedures[R]. IEPC 01-288.
[21] Biagioni B, Ceccanti F, Saverdi M, et al. Qualification Status of the FEEP-150 Electric Micropropulsion Subsystem[R]. AIAA 2005-4261.
[22] 段君毅. 场致发射电推力器工作性能及其发射机理研究[D]. 上海:上海交通大学, 2011.
[23] 高辉, 段俐, 胡良, 等. 基于镓铯对比的场发射电推力器分析与研制[J]. 推进技术, 2015, 36(2).(GAO Hui, DUAN Li, HU Liang, et al. Analysis and Development of Ga-FEEP Based on Comparison of Gallium and Cesium[J]. Journal of Propulsion Technology, 2015, 36(2).)
[24] Mitterauer J. Miniaturized Liquid Metal Ion Sources (MILMIS)[J]. IEEE Transactions on Plasma Science, 1991, 19(5): 790-799.
[25] Marcuccio S, Giusti N, Tolstoguzov A. Characte-Rization of Linear Slit FEEP Using an Ionic Liquid Propellant[R]. IEPC 2009-180.
[26] Tajmar M, Scharlemann C, Genovese A, et al. Liquid-Metal-Ion Source Development for Space Propulsion at ARC[J]. Ultramicroscopy, 2009, 109(5): 442-446.
[27] Genovese A, Buldrini N, Tajmar M, et al. Indium FEEP Cluster Development[R]. AIAA 2005-4385.
[28] 段君毅, 康小明, 赵万生. 用于场致发射电推力器的微细发射针制造技术[J]. 上海交通大学学报, 2009, 43(12): 1968-1972.
[29] Tajmar M, Jang B. New Materials and Processes for Field Emission Ion and Electron Emitters[J]. CEAS Space Journal, 2013, 4(1-4): 47-54.
[30] Hockett L A, Creager S E. A Convenient Method for Removing Surface Oxides from Tungsten STM Tips[J]. Review of Scientific Instruments, 1993, 64(1): 263-264.
[31] Vasiljevich I, Tajmar M, Buldrini N, et al. Development of a Focus Electrode for an Indium FEEP Thruster[R]. AIAA 2005-4384.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2017-03-15；修订日期:2017-06-05。基金项目:国家自然科学基金(51675341)；中国科学院微小卫星重点实验室开放课题(KFKT13SYS4)。作者简介:郭登帅,男,博士生,研究领域为场发射电推进技术与理论。E-mail: gds@sjtu.edu.cn

Development and Experimental Characteristics of Indium Needle-Type Field Emission Electric Propulsion Thruster

针式铟场发射电推力器的研制及实验特性 *

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