Volume 35 Issue 6
Jun.  2020
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2020  >  35(6): 1275-1285
FAN Yipeng, XIA Guangqing, HAN Yajie. Research progress of ionic liquid micropropulsion technology[J]. Journal of Aerospace Power, 2020, 35(6): 1275-1285. doi: 10.13224/j.cnki.jasp.2020.06.018
Citation: FAN Yipeng, XIA Guangqing, HAN Yajie. Research progress of ionic liquid micropropulsion technology[J]. Journal of Aerospace Power, 2020, 35(6): 1275-1285. doi: 10.13224/j.cnki.jasp.2020.06.018
shu

Research progress of ionic liquid micropropulsion technology

doi: 10.13224/j.cnki.jasp.2020.06.018
  • 1.

    State Key Laboratory of Structural Analysis for Industrial Equipment,Dalian University of Technology,Dalian Liaoning 116024,China

  • 2.

    Key Laboratory of Advanced Technology for Aerospace Vehicles,Liaoning Province,Dalian University of Technology,Dalian Liaoning 116024,China

  • Received Date: 2019-12-04
  • Publish Date: 2020-06-28
    Abstract
  • 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.

     

    • FullText(HTML)
  • loading
    • References(51)
  • [1]
    韩泉东,洪鑫,周海清.空间推进技术需求与发展分析［J］.火箭推进,2012,38(2):9-15. HAN Quandong,HONG Xin,ZHOU Haiqing.Analysis on requirement and development of space propulsion technology［J］.Journal of Rocket Propulsion,2012,38(2):9-15.(in Chinese)
    [2]
    SELVA D,KREJCI D.A survey and assessment of the capabilities of Cubesats for Earth observation［J］.Acta Astronautica,2012,74:50-68.
    [3]
    LEVCHENKO I,BAZAKA K,DING Y,et al.Space micropropulsion systems for Cubesats and small satellites:From proximate targets to furthermost frontiers［J］.Applied Physics Reviews,2018,5:011104.1-011104.36.
    [4]
    LOZANO P C,WARDLE B L,MOLONEY P,et al.Nanoengineered thrusters for the next giant leap in space exploration［J］.MRS(Materials Research Society) Bulletin,2015,40(10):842-849.
    [5]
    李永,刘旭辉,汪旭东,等.空间极小推力宽范围可调推进技术研究进展［J］.空间控制技术与应用,2019,45(6):1-12,19. LI Yong,LIU Xuhui,WANG Xudong,et al.Review and prospect on the large-range thrust throttling technology with extremely small thrust［J］.Aerospace Control and Application,2019,45(6):1-12,19.(in Chinese)
    [6]
    胡一鸣,梅健伟,罗俊.天琴计划与国际合作［J］.科学通报,2019,64(24):2475-2483. HU Yiming,MEI Jianwei,LUO Jun.TianQin project and international collaboration［J］.Chinese Science Bulletin,2019,64(24):2475-2483.(in Chinese)
    [7]
    COURTNEY D G,SHEA H,DANNENMAYER K,et al.Charge neutralization and direct thrust measurements from bipolar pairs of ionic electrospray thrusters［J］.Journal of Spacecraft and Rockets,2017,55(1):54-65.
    [8]
    INOUE N,NAGAO M,MURAKAMI K,et al.Fabrication of a high-density emitter array for electrospray thrusters using field emitter array process［J］.Japanese Journal of Applied Physics,2019,58(SE):1-7.
    [9]
    COURTNEY D G,DANDAVINO S,SHEA H.Comparing direct and indirect thrust measurements from passively fed ionic electrospray thrusters［J］.Journal of Propulsion and Power,2016,32(2):392-407.
    [10]
    HENNING T,HUHN K,ISBERNER L W,et al.Miniaturized electrospray thrusters［J］.IEEE Transactions on Plasma Science,2018,46(2):214-218.
    [11]
    GAROZ D,FERNANDEZ DE LA MORA J.Charge emissions from electrosprays in vacuum:Mixtures of formamide with methylammonium formate［J］.Journal of Applied Physics,2013,113(6):064901.1-064901.8.
    [12]
    ZHOU Zhaoying,XIONG Jijun,YE Xiongying,et al.Designing,fabrication,and test of a MEMS colloid thruster［J］.Technologies and Applications,2002,4928:148-154.
    [13]
    郭登帅,康小明,刘欣宇,等.场发射电推力器的研究现状及其关键技术［J］.火箭推进,2018,44(4):1-9. GUO Dengshuai,KANG Xiaoming,LIU Xinyu,et al.Research status and key technologies of field emission electric propulsion thruster［J］.Journal of Rocket Propulsion,2018,44(4):1-9.(in Chinese)
    [14]
    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. DUAN Junyi.Research on operation characteristics and emission mechanism of field emission electric propulsion thruster［D］.Shanghai:Shanghai Jiao Tong University,2011.(in Chinese)
    [15]
    GUERRA-GARCIA C,KREJCI D,LOZANO P.Spatial uniformity of the current emitted by an array of passively fed electrospray porous emitters［J］.Journal of Physics:D Applied Physics,2016,49(11):1-12.
    [16]
    DANDAVINO S,ATAMAN C,RYAN C N,et al.Microfabricated electrospray emitter arrays with integrated extractor and accelerator electrodes for the propulsion of small spacecraft［J］.Journal of Micromechanics and Microengineering,2014,24(7):075011.1-075011.13.
    [17]
    石家华,孙逊,杨春和,等.离子液体研究进展［J］.化学通报,2002,65(4):243-250. SHI Jiahua,SUN Xun,YANG Chunhe,et al.Research progress of ionic liquids［J］.Chemistry Bulletin,2002,65(4):243-250.(in Chinese)
    [18]
    ZHANG Suojiang,SUN Ning,HE Xuezhong,et al.Physical properties of ionic liquids:database and evaluation［J］.Journal of Physical and Chemical Reference Data,2006,35(4):1475-1517.
    [19]
    KREJCI D,MIER-HICKS F,MARTEL F,et al.Design and characterization of a scalable ion electrospray propulsion system［R］.International Electric Propulsion Conference,IEPC-2015-149,2015.
    [20]
    HILL F A,HEUBEL E V,PONCE DE LEON P,et al.High-throughput ionic liquid ion sources using arrays of microfabricated electrospray emitters with integrated extractor grid and carbon nanotube flow control structures［J］.Journal of Microelectromechanical Systems,2014,23(5):1237-1248.
    [21]
    ZAITSAU D H,KABO G J,STRECHAN A A,et al.Experimental vapor pressures of 1-alkyl-3-methylimidazolium bis(trifluoromethylsulfonyl)imides and a correlation scheme for estimation of vaporization enthalpies of ionic liquids［J］.The Journal of Physical Chemistry:A,2006,110(22):7303-7306.
    [22]
    LOZANO P,MARTINEZ-SANCHEZ M.Ionic liquid ion sources:characterization of externally wetted emitters［J］.Journal of Colloid and Interface Science,2005,282(2):415-421.
    [23]
    GAROZ D,BUENO C,LARRIBA C,et al.Taylor cones of ionic liquids from capillary tubes as sources of pure ions:the role of surface tension and electrical conductivity［J］.Journal of Applied Physics,2007,102(6):064913.1-064913.10.
    [24]
    TAYLOR G.Disintegration of water drops in an electric field［J］.Proceedings of the Royal Society of London.Serie,1964,280(1382):383-397.
    [25]
    DELAMORA J F,LOSCERTALES I G.The current emitted by highly conducting taylor cones［J］.Journal of Fluid Mechanics,1994,260(1):155-184.
    [26]
    BORNER A,LI Z,LEVIN D A.Prediction of fundamental properties of ionic liquid electrospray thrusters using molecular dynamics［J］.The Journal of Physical Chemistry:B,2013,117(22):6768-6781.
    [27]
    COURTNEY D G.Ionic liquid ion source emitter arrays fabricated on bulk porous substrates for spacecraft propulsion［D］.Cambridge,USA:Massachusetts Institute of Technology,2011.
    [28]
    程世豪.离子液体微型电推进器三维仿真与性能分析［D］.南京:南京航空航天大学,2017. CHENG Shihao.Three dimensional simulation and performance analysis of ionic liquid micro thruster［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2017.(in Chinese)
    [29]
    COFFMAN C,COURTNEY D G,HICKS F,et al.Progress toward a variable specific impulse electrospray propulsion system［R］.San Diego,CA,USA:the 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,2011.
    [30]
    NABITY J A,DAILY J W.Effect of ionic liquid composition on colloid thruster emission and thrust performance［J］.Journal of Propulsion and Power,2018,34(1):260-266.
    [31]
    郭云涛,李世鹏,武志文,等.离子液体电喷微推力器系统设计及性能初步研究［J］.推进技术,2020,41(1):212-219. GUO Yuntao,LI Shipeng,WU Zhiwen,et al.Design of ionic liquid electrospray micro-thruster system and preliminary study on its performance［J］.Journal of Propulsion Technology,2020,41(1):212-219.(in Chinese)
    [32]
    ROMERO -SANZ I,BOCANEGRA R,FERNANDEZ DE LA MORA J,et al.Source of heavy molecular ions based on Taylor cones of ionic liquids operating in the pure ion evaporation regime［J］.Journal of Applied Physics,2003,94(5):3599-3605.
    [33]
    BORNER A,LEVIN D A.Coupled Molecular dynamics:3-D poisson simulations of ionic liquid electrospray thrusters［J］.IEEE Transactions on Plasma Science,2015,43(1):295-304.
    [34]
    NEIL A M,DEBORAH A L.Molecular dynamics electrospray simulations of coarse-grained ethylammonium nitrate (EAN) and 1-ethyl-3-methylimidazolium tetrafluoroborate (EMIM-BF4)［J］.Aerospace,2018,5(1):1-18.
    [35]
    LEGGE R S,LOZANO P C.Electrospray propulsion based on emitters microfabricated in porous metals［J］.Journal of Propulsion and Power,2011,27(2):485-95.
    [36]
    LENGUITO G,FERNANDEZ DE LA MORA J,GOMEZ A.Scaling up the power of an electrospray microthruster［J］.Journal of Micromechanics and Microengineering,2014,24(5):055003.1-055003.10.
    [37]
    QUANG TRAN SI B,BYUN D,LEE S.Experimental and theoretical study of a cone-jet for an electrospray microthruster considering the interference effect in an array of nozzles［J］.Journal of Aerosol Science,2007,38(9):924-934.
    [38]
    COURTNEY D G,Li H Q,LOZANO P.Emission measurements from planar arrays of porous ionic liquid ion sources［J］.Journal of Physics:D Applied Physics,2012,45:485203.1-485203.13.
    [39]
    COURTNEY D G,SHEA H.Influences of porous reservoir Laplace pressure on emissions from passively fed ionic liquid electrospray sources［J］.Applied Physics Letters,2015,107(10):103504.1-103504.5.
    [40]
    RYAN C,DAYKIN-ILIOPOULOS A,STARK J,et al.Experimental progress towards the MicroThrust MEMS electrospray electric propulsion system［R］.Washington:George Washington University,2013.
    [41]
    BORNER A,LI Z,LEVIN D A.Modeling of an ionic liquid electrospray using molecular dynamics with constraints［J］.The Journal of Chemical Physics,2012,136(12):124507.1-124507.11.
    [42]
    CASTRO S,FERNANDEZ DE LA MORA J.Effect of tip curvature on ionic emissions from Taylor cones of ionic liquids from externally wetted tungsten tips［J］.Journal of Applied Physics,2009,105(3):034903.1-034903.8.
    [43]
    LOZANO P,MARTINEZ-SANCHEZ M.Efficiency estimation of EMI-BF4 ionic liquid electrospray thrusters［R］.Tucson,Arizona,USA:the 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,2005.
    [44]
    WANG P,BORNER A,LI Z,et al.An advanced particle-in-cell(PIC) approach for electrospray simulation in a colloid thruster using molecular dynamics simulation results［R］.New Orleans,Louisiana,USA:the 43rd AIAA Thermophysics Conference,2012.
    [45]
    EMOTO K,TSUCHIYA T,TAKAO Y.Numerical investigation of steady and transient ion beam extraction mechanisms for electrospray thrusters［J］.Transactions of the Japan Society for Aeronautical and Space Sciences,Aerospace Technology Japan,2018,16(2):110-115.
    [46]
    KREJCI D,MIER-HICKS F,THOMAS R,et al.Emission characteristics of passively fed electrospray microthrusters with propellant reservoirs［J］.Journal of Spacecraft and Rockets,2017,54(2):447-458.
    [47]
    COURTNEY D G,SHEA H.Fragmentation in time-of-flight spectrometry-based calculations of ionic electrospray thruster performance［J］.Journal of Propulsion and Power,2015,31(5):1500-1504.
    [48]
    KRPOUN R,SMITH K L,STARK J P W,et al.Tailoring the hydraulic impedance of out-of-plane micromachined electrospray sources with integrated electrodes［J］.Applied Physics Letters,2009,94(16):163502.1-163502.3.
    [49]
    GRUSTAN-GUTIERREZ E,GAMERO-CASTANO M.Microfabricated electrospray thruster array with high hydraulic resistance channels［J］.Journal of Propulsion and Power,2017,33(4):984-991.
    [50]
    刘欣宇,康小明,徐明明,等.阵列式离子液体电喷推力器的研制及实验特性［R］.南京:第15届中国电推进学术研讨会,2019.
    [51]
    BRIKNER N,LOZANO P C.The role of upstream distal electrodes in mitigating electrochemical degradation of ionic liquid ion sources［J］.Applied Physics Letters,2012,101(19):193504.1-193504.4.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(2204.0KB)
    XML

    Article Metrics

    Article views (873) PDF downloads(500) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return