高电压霍尔推力器技术发展展望
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- 英文论文题名：Review and Prospect of High-Voltage Hall Effect Thrusters
- 论文作者：程佳兵 ; 康小录 ; 杭观荣 ; 余水淋
- 英文论文作者：Cheng Jiabing ; Kang Xiaolu ; Hang Guanrong ; Yu Shuilin ; Shanghai Institute of Space Propulsion ; Shanghai Engineering Research Center of Space Engine
- 年：2016
- 作者机构：上海空间推进研究所;上海空间发动机工程技术研究中心;
- 论文关键词：霍尔推力器 ; 高电压 ; 高比冲 ; 放电特性
- 英文论文关键词：Hall Effect Thrusters ; high-voltage ; High-impulse ; Discharge characteristic
- 会议召开时间：2016-08-17
- 会议录名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议论文集
- 语种：中文
- 分类号：V439.4
- 学会代码：HTDZ
- 会议名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议
- 会议地点：中国陕西西安
- 主办单位：中国航天第三专业信息网、中国航天科技集团公司科技委、中国航天科工集团公司科技委
- 学会名称：中国航天第三专业信息网
- 页数：10
- 文件大小：1830k
- 原文格式：D
- 会议级别：全国
摘要
近年来,随着霍尔推力器在航天器上的大量应用,进一步提高其比冲性能已成为拓展霍尔推力器应用领域的重要研究方向。分析表明:放电电压是决定霍尔推力器比冲的主要因素,因此高电压霍尔推力器的研究受到了广泛关注。本文概述了国际上高电压霍尔推力器研究进展,主要涉及高电压下的性能以及放电特性研究两个方面。具体论述了电子温度、电离区位置等内部参数的变化,以及高电压下磁场与电压的匹配、优化等问题的研究。针对当前研究工作的现状,提出了下一步高电压霍尔推力器的努力方向。
Hall Effect Thrusters(HET) are widely applied in spacecrafts in recent years, and further improvement of the specific-impulse has become an important direction of the development of the HET. It is proved that discharge voltage is the main factor which determines the specific impulse of HET, therefore the study of the high-voltage has attracted extensive attention. In this paper, the research situation and progress are reviewed in the aspects of performance and discharge characteristics at high-voltage conditions. Discharge characteristic parameters(such as electron temperature and the location of ionization region), magnetic field matching and optimization problem are discussed. Considering the defects of current studies, some suggestions are given on high-voltage HET.
Hall Effect Thrusters(HET) are widely applied in spacecrafts in recent years, and further improvement of the specific-impulse has become an important direction of the development of the HET. It is proved that discharge voltage is the main factor which determines the specific impulse of HET, therefore the study of the high-voltage has attracted extensive attention. In this paper, the research situation and progress are reviewed in the aspects of performance and discharge characteristics at high-voltage conditions. Discharge characteristic parameters(such as electron temperature and the location of ionization region), magnetic field matching and optimization problem are discussed. Considering the defects of current studies, some suggestions are given on high-voltage HET.
引文
[1]于达仁等著.空间电推进原理.哈尔滨工业大学出版社,2014.3.
[2]杭观荣,康小录.国外多模式霍尔电推进发展概况及启示.火箭推进.2014.4.
[3]David Manzella,David Jacobson,Robert Jankovsky.High Voltage SPT Performance,AIAA-2001-3774.
[4]Hofer R R.Development and characterization of high-efficiency,high-specific impulse xenon Hall thrusters.Thesis for Doctor’s Degree.University of Michigan.2004.
[5]Popov G,Kim V,Kozlov V et al.Investigation of the possibility to create the stationary plasma thrusters(SPT)with high specific impulse.62nd international astronautical congress.2011.1122.
[6]Hofer R R,Gallimore A D.The Role of Magnetic Field Topography in Improving the Performance of High-Voltage Hall Thrusters,AIAA-2002-4111.
[7]Colleen M.Marrese,James M.Haas et al.The D100 performance and plume characterization on krypton.AIAA96-969.
[8]Gorshkov O A,Muravlev V A,Shagaida A A.Hall and Ion Thrusters for Spacecraft-Moscow,“Mashinostroyeniye”,2008(In Russsia).
[9]Hofer R R,Jankovsky R S.The influence of current density and magnetic field topography in optimizing the performance,divergence,and plasma oscillations of high specific impulse hall thrusters.IEPC-2003-142.
[10]Szabo J J,Azziz Y.Characterization of a High Specific Impulse Xenon Hall Effect Thruster.IEPC-2005-324.
[11]Albarède L et al.Characteristics of PPS-1350 type thrusters under increased discharge voltages and comparison with hybrid codes simulation results.IEPC-2005-136.
[12]Takahata Y et al.Research and development of high-power,high-specific-impulse magnetic-layer-type hall thrusters for Manned Mars exploration.IEPC-2015-151.
[13]王真容,丁永杰.高电压下霍尔推力器放电通道的数值模拟.第七届中国电推进技术学术研讨会.深圳,2011.
[14]Kamhawi H,Haag T,Pinero L.Overview of the Development of a Low Cost High Voltage Hall Accelerator Propulsion System for NASA Science Mission[R].AIAA 2011-5520,2011.
[15]冯桃君,姜利祥等.电推进技术的发展及应用.第十一届中国电推进技术学术研讨会.北京,2015.
[16]张天平,张雪儿等.空间电推进技术及应用新进展.真空与低温.2013(4):187-194.
[17]Jankovsky R S,Jacobson D T,et al.NASA’s Hall Thruster Program 2002[C].38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Indianapolis,Indiana.TM-2002-211880.
[18]Soulas G C,Haag T W,et al.Performance test results of the NASA-457Mv2 Hall thruster[J].AIAA Paper,2012,3940.
[19]Colleen Marrese-Reading,Anita Sengupta.et al.The VHITAL program to demonstrate the performance and lifetime of a Bismuth-Fueled very high Isp hall thruster.AIAA 2005-4564.
[20]Semenkin A V,et al.Overview of electric propels-ion activity in Russia.IEPC-2007-275.
[21]Barral S,Makowski K,Peradzynski Z,Gascon N,and Dudeck M.Wall material effects in stationary plasma thrusters.II.Near-wall and in-wall conductivity.Physics of Plasmas 10,4137(2003).
[22]Ahedo E,Gallardo J M,and Martinez-Sanchez M.Effects of the dielectric walls on the axial discharge of a hall thruster.AIAA 2002-4244.
[23]E.Ahedo and D.Escobar.Influence of design and operation parameters on hall thruster performance.Journal of Applied Physics.96,983(2004).
[24]Raitses Y,et al.Space charged saturated sheath regime and electron temperature saturation in Hall thrusters.Physics of Plasmas[J],12,073507(2005).
[25]Raitses Y,Smirnov A,Staack D,and Fisch N J,Measurements of Secondary Electron Emission Effects in the Hall Thruster Discharge.Physics of Plasmas.13,014502(2006).
[26]Pote B,Tedrake R.Performance of a High Specific Impulse Hall Thruster[C].IEPC-01-35.
[27]Kim V.Main Physical Features and Processes Determining the Performance of Stationary Plasma Thrusters[J].Journal of Propulsion and Power,1998,14(5):736-743.
[28]鄂鹏等.磁场强度对霍尔推力器放电特性影响的实验研究.物理学报.Vol.58,No.4.
[29]Morozov A I,Esipchuk Y V,Kapulkin A M,et al.Effect of the Magnetic Field on a Closed-electron-drift Accelerator[J].Soviet Physics-Technical Physics,1972,17(3):482–487.
[30]Garrigues L,Hagelaar G J M,et al.Model study of the influence of the magnetic field configuration on the performance and lifetime of a hall thruster.Physics of Plasmas.2003,10(12):4886-4892.
[31]Morozov A I,Bugrova A I,et al.ATON-thruster plasma accelerator.Plasma Physics Reports.1997,23(7):587-597.
[32]Keidar M,Boyd I D,et al.Plasma flow and plasma-wall transition in Hall thruster channel.Physics of Plasmas.2001,8(12):5315-5322.
[33]Hirokazu Tahara,Katsumi Imanaka and Seiro Yuge,Effects of channel wall material on thrust performance and plasma characteristics of Hall-effect thru-sters.Vacuum.2006,80(11-12):1216-1222.
[34]Bugrova A I,Morozov A I,Kharchevnikov V K.Experimental Investigation of Near Wall Conductivity[J].Soviet Journal of Plasma Physics,1990,16(12):849–856.
[35]Roche S,Barra S,Bechu S.Thermal analysis of a stationary plasma thruster[R].AIAA 99-2296,1992.
[2]杭观荣,康小录.国外多模式霍尔电推进发展概况及启示.火箭推进.2014.4.
[3]David Manzella,David Jacobson,Robert Jankovsky.High Voltage SPT Performance,AIAA-2001-3774.
[4]Hofer R R.Development and characterization of high-efficiency,high-specific impulse xenon Hall thrusters.Thesis for Doctor’s Degree.University of Michigan.2004.
[5]Popov G,Kim V,Kozlov V et al.Investigation of the possibility to create the stationary plasma thrusters(SPT)with high specific impulse.62nd international astronautical congress.2011.1122.
[6]Hofer R R,Gallimore A D.The Role of Magnetic Field Topography in Improving the Performance of High-Voltage Hall Thrusters,AIAA-2002-4111.
[7]Colleen M.Marrese,James M.Haas et al.The D100 performance and plume characterization on krypton.AIAA96-969.
[8]Gorshkov O A,Muravlev V A,Shagaida A A.Hall and Ion Thrusters for Spacecraft-Moscow,“Mashinostroyeniye”,2008(In Russsia).
[9]Hofer R R,Jankovsky R S.The influence of current density and magnetic field topography in optimizing the performance,divergence,and plasma oscillations of high specific impulse hall thrusters.IEPC-2003-142.
[10]Szabo J J,Azziz Y.Characterization of a High Specific Impulse Xenon Hall Effect Thruster.IEPC-2005-324.
[11]Albarède L et al.Characteristics of PPS-1350 type thrusters under increased discharge voltages and comparison with hybrid codes simulation results.IEPC-2005-136.
[12]Takahata Y et al.Research and development of high-power,high-specific-impulse magnetic-layer-type hall thrusters for Manned Mars exploration.IEPC-2015-151.
[13]王真容,丁永杰.高电压下霍尔推力器放电通道的数值模拟.第七届中国电推进技术学术研讨会.深圳,2011.
[14]Kamhawi H,Haag T,Pinero L.Overview of the Development of a Low Cost High Voltage Hall Accelerator Propulsion System for NASA Science Mission[R].AIAA 2011-5520,2011.
[15]冯桃君,姜利祥等.电推进技术的发展及应用.第十一届中国电推进技术学术研讨会.北京,2015.
[16]张天平,张雪儿等.空间电推进技术及应用新进展.真空与低温.2013(4):187-194.
[17]Jankovsky R S,Jacobson D T,et al.NASA’s Hall Thruster Program 2002[C].38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Indianapolis,Indiana.TM-2002-211880.
[18]Soulas G C,Haag T W,et al.Performance test results of the NASA-457Mv2 Hall thruster[J].AIAA Paper,2012,3940.
[19]Colleen Marrese-Reading,Anita Sengupta.et al.The VHITAL program to demonstrate the performance and lifetime of a Bismuth-Fueled very high Isp hall thruster.AIAA 2005-4564.
[20]Semenkin A V,et al.Overview of electric propels-ion activity in Russia.IEPC-2007-275.
[21]Barral S,Makowski K,Peradzynski Z,Gascon N,and Dudeck M.Wall material effects in stationary plasma thrusters.II.Near-wall and in-wall conductivity.Physics of Plasmas 10,4137(2003).
[22]Ahedo E,Gallardo J M,and Martinez-Sanchez M.Effects of the dielectric walls on the axial discharge of a hall thruster.AIAA 2002-4244.
[23]E.Ahedo and D.Escobar.Influence of design and operation parameters on hall thruster performance.Journal of Applied Physics.96,983(2004).
[24]Raitses Y,et al.Space charged saturated sheath regime and electron temperature saturation in Hall thrusters.Physics of Plasmas[J],12,073507(2005).
[25]Raitses Y,Smirnov A,Staack D,and Fisch N J,Measurements of Secondary Electron Emission Effects in the Hall Thruster Discharge.Physics of Plasmas.13,014502(2006).
[26]Pote B,Tedrake R.Performance of a High Specific Impulse Hall Thruster[C].IEPC-01-35.
[27]Kim V.Main Physical Features and Processes Determining the Performance of Stationary Plasma Thrusters[J].Journal of Propulsion and Power,1998,14(5):736-743.
[28]鄂鹏等.磁场强度对霍尔推力器放电特性影响的实验研究.物理学报.Vol.58,No.4.
[29]Morozov A I,Esipchuk Y V,Kapulkin A M,et al.Effect of the Magnetic Field on a Closed-electron-drift Accelerator[J].Soviet Physics-Technical Physics,1972,17(3):482–487.
[30]Garrigues L,Hagelaar G J M,et al.Model study of the influence of the magnetic field configuration on the performance and lifetime of a hall thruster.Physics of Plasmas.2003,10(12):4886-4892.
[31]Morozov A I,Bugrova A I,et al.ATON-thruster plasma accelerator.Plasma Physics Reports.1997,23(7):587-597.
[32]Keidar M,Boyd I D,et al.Plasma flow and plasma-wall transition in Hall thruster channel.Physics of Plasmas.2001,8(12):5315-5322.
[33]Hirokazu Tahara,Katsumi Imanaka and Seiro Yuge,Effects of channel wall material on thrust performance and plasma characteristics of Hall-effect thru-sters.Vacuum.2006,80(11-12):1216-1222.
[34]Bugrova A I,Morozov A I,Kharchevnikov V K.Experimental Investigation of Near Wall Conductivity[J].Soviet Journal of Plasma Physics,1990,16(12):849–856.
[35]Roche S,Barra S,Bechu S.Thermal analysis of a stationary plasma thruster[R].AIAA 99-2296,1992.
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