碘工质霍尔推力器原理与研究进展
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摘要
霍尔效应推力器作为一种先进的电推进装置受到国内外航天界的广泛关注,利用氙气作为推进剂的中功率霍尔推进技术已相对成熟,并有上千台霍尔推力器在轨运行。然而,作为一种稀有气体,高纯度氙气价格昂贵,相对固体推进剂其储存密度偏低,高压储箱给安全和减重带来不利。因此,寻求一种新型固态工质替代氙气具有重要意义。2006年,有学者提出利用固态碘特有的升华和电离特性,可以代替氙气作为霍尔推力器的推进剂的想法,并对此进行了原理样机设计和初步实验研究。首先对国外的研究进展和目前能达到的推力器性能进行了概述,接着阐述了碘工质霍尔推力器的工作原理,然后总结了该推力器研究的关键技术和理论上可行的解决方案,最后对碘工质霍尔推力器的应用前景进行了展望。
Hall effect thruster as an advanced electric propulsion device has received extensive attention in the space community all over the world. The medium power hall propulsion technology with xenon is relatively mature,and there have been thousands of hall thrusters in orbit. However,as a noble gas,high-purity xenon is expensive. Its storage density is lower than solid propellant,and the high pressure storage tank causes negative effects to safety and weight loss. Therefore,it is very meaningful to seek a new type of solid operating medium instead of xenon. In 2006,some scholars put forward the idea that the solid iodine can replace xenon as the propellant of the hall thruster based on the unique sublimation and ionization properties. They also carried out the principle prototype design and preliminary experimental study. Firstly, the research progress abroad and the present performance of the thruster were stated. Secondly,the working principle of hall thruster was described. Thirdly,the key technology and the theoretically feasible solution were summarized. The prospect of applications was also commented here.
Hall effect thruster as an advanced electric propulsion device has received extensive attention in the space community all over the world. The medium power hall propulsion technology with xenon is relatively mature,and there have been thousands of hall thrusters in orbit. However,as a noble gas,high-purity xenon is expensive. Its storage density is lower than solid propellant,and the high pressure storage tank causes negative effects to safety and weight loss. Therefore,it is very meaningful to seek a new type of solid operating medium instead of xenon. In 2006,some scholars put forward the idea that the solid iodine can replace xenon as the propellant of the hall thruster based on the unique sublimation and ionization properties. They also carried out the principle prototype design and preliminary experimental study. Firstly, the research progress abroad and the present performance of the thruster were stated. Secondly,the working principle of hall thruster was described. Thirdly,the key technology and the theoretically feasible solution were summarized. The prospect of applications was also commented here.
引文
[1]康小录,杭观荣,朱智春.霍尔电推进技术的发展与应用[J].火箭推进,2017,43(1):8-17.KANG X L,HANG G R,ZHU Z C.Development and application of Hall electric propulsion technology[J].Journal of Rocket Propulsion,2017,43(1):8-17.
[2]杭观荣,康小录.国外多模式霍尔电推进发展概况及启示[J].火箭推进,2014,40(2):1-6.HANG G R,KANG X L.Development overview of foreign multimode Hall electric propulsion technology and corresponding inspiration[J].Journal of Rocket Propulsion,2014,40(2):1-6.
[3]SZABO J,POTE B,PAINTAL S,et al.Performance evaluation of an Iodine vapor Hall thruster[J].Journal of Propulsion and Power,2012,28(4):848-857.
[4]POTE B,TEDRAKE R.Performance of a high specific impulse Hall thruster,IEPC-01-35[C]//27th International Electric Propulsion Conference.California:IEPC,2001.
[5]SZABO J,ROBIN M,PAINTAL S,et al.High density Hall thruster propellant investigations[C]//48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exhibit.Atlanta:AIAA,2012.
[6]SZABO J,ROBIN M,PAINTAL S,et al.Iodine propellant space propulsion,IEPC-2013-311[C]//33rd International Electric Propulsion Conference.Washington:IEPC,2013.
[7]SZABO J,POTE B,BYRNE L,et al.Eight kilowatt Hall thruster system characterization,IEPC-2013-317[C]//33rd International Electric Propulsion Conference.Washington:IEPC,2013.
[8]刘辉,牛翔,李鑫,等.碘工质电推进技术研究综述[J].推进技术,2019,40(1):12-25.
[9]KAMHAWI H,HAAG T,BENAVIDES G,et al.Overview of iodine propellant Hall thruster development activities at NASA Glenn research center[C]//52nd AIAA/SAE/AS-EE Joint Propulsion Conference.Salt Lake City,UT:AIAA,2016.
[10]TIMOTHY D S,KAMHAWI H,HICKMAN T,et al.O-verview of NASA iodine Hall thruster propulsion system development[C]//Space Propulsion.Rome:[s.n.],2016.
[11]MCGUIRE M L,OLESON S R.Concurrent Mission and systems design at NASA glenn research center:the origins of the COMPASS team[C]//AIAA SPACE 2011 Conference&Exposition.Long Beach,California:AIAA,2011.
[12]SZABO J,TEDRAKE R,METIVIER E,et al.Characterization of a one hundred watt,long lifetime Hall effect thruster for small spacecraft[C]//53rd AIAA/SAE/AS-EE Joint Propulsion Conference.Atlanta:AIAA,2017.
[13]HILLIER A.Revolutionizing space propulsion through the characterization of iodine as fuel for Hall-effect thrusters[D].Ohio:Air Force Institute of Technology,2011.
[14]DANKANICH J W,SELBY M,POLZIN K A,et al.The iodine satellite(i Sat)project development towards critical design review(CDR)[C]//52nd AIAA/SAE/ASEEJoint Propulsion Conference.Salt Lake City,UT:AIAA,2016.
[15]RAND L P,WILLIAMS J D.Instant start electride hollow cathode,IEPC-2013-305[C]//33rd International E-lectric Propulsion Conference.Washington:IEPC,2013.
[16]PRINCE B D,BEMISH R J,LEVANDIER D J.Application of a first generation collisional radiative model for iodine to optical emissions from the plume of an iodine Hall effect thruster[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Atlanta:AIAA,2017.
[17]DRESSLER R A,CHIU Y,LEVANDIER D J.Propellant alternatives for ion and Hall effect thrusters[C]//38th Aerospace Sciences Meeting and Exhibit.Reno,NV:AIAA,2000.
[18]SZABO J,ROBIN M.Plasma species measurements in the plume of an Iodine fueled hall thruster[J].Journal of Propulsion and Power,2014,30(5):1357-1367.
[19]ALI M,KIM Y.Ionization cross sections by electron impact on halogen atoms,diatomic halogen and Hydrogen halide molecules[J].Journal of Physics B,2008,41(14):1-12.
[20]JOSHIPURA K N.Theoretical total ionization cross-sections for electron impact on atomic and molecular halogens[J].International Journal of Mass Spectrometry,2002,216(3):239-247.
[21]HATES T R,WETZEL R,FREUND R.absolute electronimpact ionization cross-section measurements of the halogen atoms[J].Physical Review A,1987,35(2):578-584.
[22]SYAGE J A.Electron-impact cross sections for multiple ionization of Kr and Xe[J].Physical Review A,1992,46(9):5666-5679.
[23]LEROY R,BERNSTEIN R.Dissociation energies of diatomic molecules from vibrational spacings of higher levels:application to the halogens[J].Chemical Physics Letters,1970,5(1):42-44.
[24]SZABO J,WARNER N,MARTINEZ S M,et al.A full particle in cell simulation methodology for axisymmetric Hall effect thrusters[J].Journal of Propulsion and Power,2014,30(1):197-208.
[25]PARRA F I,AHEDO E,FIFE J M,et al.A two-dimensional hybrid model of the Hall thruster discharge[J].Journal of Applied Physics,2006,100(2):1-11.
[26]SZABO J,ROBIN M,PAINTAL S,et al.Iodine plasma propulsion test results at 1-10kW[J].IEEE Transactions on Plasma Science,2015,43(1):141-148.
[2]杭观荣,康小录.国外多模式霍尔电推进发展概况及启示[J].火箭推进,2014,40(2):1-6.HANG G R,KANG X L.Development overview of foreign multimode Hall electric propulsion technology and corresponding inspiration[J].Journal of Rocket Propulsion,2014,40(2):1-6.
[3]SZABO J,POTE B,PAINTAL S,et al.Performance evaluation of an Iodine vapor Hall thruster[J].Journal of Propulsion and Power,2012,28(4):848-857.
[4]POTE B,TEDRAKE R.Performance of a high specific impulse Hall thruster,IEPC-01-35[C]//27th International Electric Propulsion Conference.California:IEPC,2001.
[5]SZABO J,ROBIN M,PAINTAL S,et al.High density Hall thruster propellant investigations[C]//48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference&Exhibit.Atlanta:AIAA,2012.
[6]SZABO J,ROBIN M,PAINTAL S,et al.Iodine propellant space propulsion,IEPC-2013-311[C]//33rd International Electric Propulsion Conference.Washington:IEPC,2013.
[7]SZABO J,POTE B,BYRNE L,et al.Eight kilowatt Hall thruster system characterization,IEPC-2013-317[C]//33rd International Electric Propulsion Conference.Washington:IEPC,2013.
[8]刘辉,牛翔,李鑫,等.碘工质电推进技术研究综述[J].推进技术,2019,40(1):12-25.
[9]KAMHAWI H,HAAG T,BENAVIDES G,et al.Overview of iodine propellant Hall thruster development activities at NASA Glenn research center[C]//52nd AIAA/SAE/AS-EE Joint Propulsion Conference.Salt Lake City,UT:AIAA,2016.
[10]TIMOTHY D S,KAMHAWI H,HICKMAN T,et al.O-verview of NASA iodine Hall thruster propulsion system development[C]//Space Propulsion.Rome:[s.n.],2016.
[11]MCGUIRE M L,OLESON S R.Concurrent Mission and systems design at NASA glenn research center:the origins of the COMPASS team[C]//AIAA SPACE 2011 Conference&Exposition.Long Beach,California:AIAA,2011.
[12]SZABO J,TEDRAKE R,METIVIER E,et al.Characterization of a one hundred watt,long lifetime Hall effect thruster for small spacecraft[C]//53rd AIAA/SAE/AS-EE Joint Propulsion Conference.Atlanta:AIAA,2017.
[13]HILLIER A.Revolutionizing space propulsion through the characterization of iodine as fuel for Hall-effect thrusters[D].Ohio:Air Force Institute of Technology,2011.
[14]DANKANICH J W,SELBY M,POLZIN K A,et al.The iodine satellite(i Sat)project development towards critical design review(CDR)[C]//52nd AIAA/SAE/ASEEJoint Propulsion Conference.Salt Lake City,UT:AIAA,2016.
[15]RAND L P,WILLIAMS J D.Instant start electride hollow cathode,IEPC-2013-305[C]//33rd International E-lectric Propulsion Conference.Washington:IEPC,2013.
[16]PRINCE B D,BEMISH R J,LEVANDIER D J.Application of a first generation collisional radiative model for iodine to optical emissions from the plume of an iodine Hall effect thruster[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Atlanta:AIAA,2017.
[17]DRESSLER R A,CHIU Y,LEVANDIER D J.Propellant alternatives for ion and Hall effect thrusters[C]//38th Aerospace Sciences Meeting and Exhibit.Reno,NV:AIAA,2000.
[18]SZABO J,ROBIN M.Plasma species measurements in the plume of an Iodine fueled hall thruster[J].Journal of Propulsion and Power,2014,30(5):1357-1367.
[19]ALI M,KIM Y.Ionization cross sections by electron impact on halogen atoms,diatomic halogen and Hydrogen halide molecules[J].Journal of Physics B,2008,41(14):1-12.
[20]JOSHIPURA K N.Theoretical total ionization cross-sections for electron impact on atomic and molecular halogens[J].International Journal of Mass Spectrometry,2002,216(3):239-247.
[21]HATES T R,WETZEL R,FREUND R.absolute electronimpact ionization cross-section measurements of the halogen atoms[J].Physical Review A,1987,35(2):578-584.
[22]SYAGE J A.Electron-impact cross sections for multiple ionization of Kr and Xe[J].Physical Review A,1992,46(9):5666-5679.
[23]LEROY R,BERNSTEIN R.Dissociation energies of diatomic molecules from vibrational spacings of higher levels:application to the halogens[J].Chemical Physics Letters,1970,5(1):42-44.
[24]SZABO J,WARNER N,MARTINEZ S M,et al.A full particle in cell simulation methodology for axisymmetric Hall effect thrusters[J].Journal of Propulsion and Power,2014,30(1):197-208.
[25]PARRA F I,AHEDO E,FIFE J M,et al.A two-dimensional hybrid model of the Hall thruster discharge[J].Journal of Applied Physics,2006,100(2):1-11.
[26]SZABO J,ROBIN M,PAINTAL S,et al.Iodine plasma propulsion test results at 1-10kW[J].IEEE Transactions on Plasma Science,2015,43(1):141-148.