校准型Faraday探针的研制及其在SPT束流诊断上的应用
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摘要
本文针对裸Faraday探针不能准确测量等离子体束流密度分布的情况进行了分析,进而优化设计出校准型Faraday探针。
由于定向羽流离子与背景气体中的随机低速中性粒子发生了电荷交换碰撞,产生了低能离子。这些低能离子会影响Faraday探针测量羽流中离子束流密度分布的真实性。因此有必要设计校准型Faraday探针,来过滤电荷交换碰撞产生的低能离子。使得无论设备以什么样的抽速工作,都能用校准型Faraday探针,得到霍尔推力器发出的等离子体羽流中真实的离子流密度分布。
本着提高Faraday探针测试精度的设计准则,首先,全面分析了Faraday探针工作的基本工作原理、物理过程和相关工作机制,并提出了一些必要的假设来简化物理过程,以便于理论公式的推导。在此基础上进行了与校准探针基本结构设计有关的比例因子公式推导。接着,按照理论上推导的比例因子公式,确定校准Faraday探针的结构和尺寸。选择校准探针中裸探针和校准筒的材料,进行加工、安装。
然后接好测试电路,在一个真空度范围为1.7-2.3×10~(-3)Pa的真空舱里,用一个裸探针和一个校准探针来进行试验。选定801所研制的霍尔推力器工程样机SPT-70进行放电,该发动机功率约为0.6KW,放电时阴极流率为2sccm,阳极流率为16-20sccm。在加偏置电压和不加偏置电压的情况下,对两个探针做性能评估。
通过分析试验结果,不仅验证了校准探针预期的性能,即校准型Faraday探针可以过滤电荷交换碰撞产生的低能离子,测得较为真实的离子束流密度分布;还发现了在校准探针的校准筒内探针与等离子体发生了强烈的相互作用,本文从校准筒内部压力和电场等方面进行了分析。
本文最后对试验中发现的问题,提出了继续研究的手段和方法,以期能够了解探针内部情况,对探针结构和材料进一步进行优化设计,使校准型Faraday探针可以达到准确测量霍尔推力器羽流的成熟水平。
The reason why a nude Faraday probe can' t truly measure the ion current density in Hall thruster is discussed and the design of a collimated Faraday probe is reported in this paper.
The resonant charge exchange(CEX) collisions of directed plume ions with the random background population of neutrals will bring low energy ion,which will be recorded as ion current by Faraday probe.A collimated probe design is attractive because it offers the possibility of obtaining the true ion current density profile regardless of the facility pumping speed.
For improving the measuring precision of Faraday probe,firstly the paper analyses the basic principle and the physics process of plasma plume diagnose with it.Then it provides some assumptions to simplify the physics processes.Based on these assumptions,the expressions for the scale factor are derived.The structure and the size of the Faraday probe is decided by these theoretical expressions.Also the materials of the collector inside the collimated probe and the collimated tube are chosen.After all, the processing and fixing for the accessories of the collimated probe were be finished in 801 Institute.
Experiments were conducted using a traditional nude Faraday probe and a collimated probe.The probes are evaluated using a 660W Hall thruster(SPT-70,which is made in 801 Institute.) in a facility capable of maintaining background pressures of 1.7-2.3×10~(-2) Pa for cathode flow rates of 2sccm and anode flow rates of 16-20sccm. After preparing testing circuit,measurements were made for each position with the two probes either floating or biased to the collectors to evaluate them.
Detailed examination of the results has shown that the collimator can act primarily as a filter for low energy ions introduced in the plume by charge exchange collisions and the collimated probe is interacting strongly with the plasma inside the collimator. The pressure and electric fields inside the collimator are considered in this paper.
Finally other investigations may interrogate the probe interior itself by measuring the internal pressure and plasma properties with ionization gauges and electrostatic probes.Numerical modeling of the probe is also being considered,as are alternative designs to the probe geometry and materials.Further study is required to bring the collimated Faraday probe to a maturity level sufficient for use in evaluating Hall thruster plumes.
由于定向羽流离子与背景气体中的随机低速中性粒子发生了电荷交换碰撞,产生了低能离子。这些低能离子会影响Faraday探针测量羽流中离子束流密度分布的真实性。因此有必要设计校准型Faraday探针,来过滤电荷交换碰撞产生的低能离子。使得无论设备以什么样的抽速工作,都能用校准型Faraday探针,得到霍尔推力器发出的等离子体羽流中真实的离子流密度分布。
本着提高Faraday探针测试精度的设计准则,首先,全面分析了Faraday探针工作的基本工作原理、物理过程和相关工作机制,并提出了一些必要的假设来简化物理过程,以便于理论公式的推导。在此基础上进行了与校准探针基本结构设计有关的比例因子公式推导。接着,按照理论上推导的比例因子公式,确定校准Faraday探针的结构和尺寸。选择校准探针中裸探针和校准筒的材料,进行加工、安装。
然后接好测试电路,在一个真空度范围为1.7-2.3×10~(-3)Pa的真空舱里,用一个裸探针和一个校准探针来进行试验。选定801所研制的霍尔推力器工程样机SPT-70进行放电,该发动机功率约为0.6KW,放电时阴极流率为2sccm,阳极流率为16-20sccm。在加偏置电压和不加偏置电压的情况下,对两个探针做性能评估。
通过分析试验结果,不仅验证了校准探针预期的性能,即校准型Faraday探针可以过滤电荷交换碰撞产生的低能离子,测得较为真实的离子束流密度分布;还发现了在校准探针的校准筒内探针与等离子体发生了强烈的相互作用,本文从校准筒内部压力和电场等方面进行了分析。
本文最后对试验中发现的问题,提出了继续研究的手段和方法,以期能够了解探针内部情况,对探针结构和材料进一步进行优化设计,使校准型Faraday探针可以达到准确测量霍尔推力器羽流的成熟水平。
The reason why a nude Faraday probe can' t truly measure the ion current density in Hall thruster is discussed and the design of a collimated Faraday probe is reported in this paper.
The resonant charge exchange(CEX) collisions of directed plume ions with the random background population of neutrals will bring low energy ion,which will be recorded as ion current by Faraday probe.A collimated probe design is attractive because it offers the possibility of obtaining the true ion current density profile regardless of the facility pumping speed.
For improving the measuring precision of Faraday probe,firstly the paper analyses the basic principle and the physics process of plasma plume diagnose with it.Then it provides some assumptions to simplify the physics processes.Based on these assumptions,the expressions for the scale factor are derived.The structure and the size of the Faraday probe is decided by these theoretical expressions.Also the materials of the collector inside the collimated probe and the collimated tube are chosen.After all, the processing and fixing for the accessories of the collimated probe were be finished in 801 Institute.
Experiments were conducted using a traditional nude Faraday probe and a collimated probe.The probes are evaluated using a 660W Hall thruster(SPT-70,which is made in 801 Institute.) in a facility capable of maintaining background pressures of 1.7-2.3×10~(-2) Pa for cathode flow rates of 2sccm and anode flow rates of 16-20sccm. After preparing testing circuit,measurements were made for each position with the two probes either floating or biased to the collectors to evaluate them.
Detailed examination of the results has shown that the collimator can act primarily as a filter for low energy ions introduced in the plume by charge exchange collisions and the collimated probe is interacting strongly with the plasma inside the collimator. The pressure and electric fields inside the collimator are considered in this paper.
Finally other investigations may interrogate the probe interior itself by measuring the internal pressure and plasma properties with ionization gauges and electrostatic probes.Numerical modeling of the probe is also being considered,as are alternative designs to the probe geometry and materials.Further study is required to bring the collimated Faraday probe to a maturity level sufficient for use in evaluating Hall thruster plumes.
引文
[1]余水林,霍尔推力器设计、实验与内部过程模拟,上海航天局第801研究所内部资料,2004.2
[2]施晨毅,康小录,霍尔推力器的发展与设计,上海航天,2007.12
[3]施晨毅,康小录,霍尔推力器的空间应用,上海航天2007.12
[4]魏延明,电推进技术的发展研究,航天工业总公司第502研究所,1999
[5]康小录,霍尔电推进系统应用分析,上海航天局第801研究所内部资料,2002.4
[6]康小录,“空间电推进技术研究”课题技术总结,中国国防科学技术报告,2002.10
[7]Oleson S.,Myers R.,Kluever C.,Riehl J.,Curran F.,Advanced Propulsion for Geostationary Orbit Insertion and North-South Station Keeping,AIAA-95-2513
[8]Gulezinski F.S.,Spores R.A.,Analysis of Hall-Effect Thrusters and Ion Engines for Orbit Transfer Mission,AIAA-96-2973
[9]G.Saccoccia,Electric Propulsion in Europe:Current Developments and Missons,AIAA-98-3177
[10]R.M.Myers,R.J.Cassady,Overview of Major U.S.Industrial Programs in Electric Propulsion,AIAA-98-3179
[11]Rodney L.Burton,Overview of US Academic Programs in Electric Propulsion,AIAA-98-3182
[12]Frank Stanley,Examination of The Structure and Evolution of Ion Energy Properties of a 5 kW Class Laboratory Hall Effect Thruster at Various Operational Conditions,a Doctoral Dissertation of The University of Michigan,1999
[13]廖宏图,稳态等离子体推力器理论研究,中国国防科学技术报告,2001.3
[14]James Matthew,Low-Perturbation Interrogation of The Internal and Near Field Plasma Structure of a Hall Thruster Using a High Speed Probe Positioning System,a doctoral dissertation of the university of Michigan,2001
[15]Hutchinson I.,Principles of Plasma Diagonostics,Cambridge University Press,New York 1987
[16]Jankovsky,R.S.,Jacobson D.T.,Mason L.S.,Rawlin V.K.,Mantenieks,M.A.,Manzella D.H.,Hofer R.R.,Peterson P.Y.,NASA's Hall Thruster Program,AIAA-2001-3888
[17]R.Joseph Cassady,Overview of Major US Industrial Programs in Electric Propulsion,AIAA 2001-3226,July 2001;
[18]R.A.Spores,Overview of the USAF Electric Propulsion Program,AIAA 2001-3225,July 2001;
[19]G.Saccoccia,Overview of European Electric Propulsion Activities,AIAA 2001-3228,July 2001;
[20]O.A.Gorshkov,Overview of Russian Activities in Electric Propulsion,AIAA 2001-3229,July 2001;
[21]J.Dunning,NASA's Electric Propulsion Program:Technology Investments for the New Millenium,AIAA 2001-3224,July 2001.
[22]Alec D.Gallimore,Review of the EP Activities of US Academia Compiled and Edited,AIAA-2001-3227;
[23]王正,HET性能实验报告,上海航天局第801研究所内部资料,2003
[24]饶雨生,等离子体物理基础,西安交通大学出版社,2000[30]
[25]甄汉生,等离子体加工技术,清华出版社,1992
[26]王正,HET性能优化设计报告,上海航天局第801研究所内部资料,2003
[27]王正,廖宏图,康小录,稳态等离子体(SPT)束流及等离子体诊断装置的研制和应用,总装2002推进会议
[28]余水林,Hall推力器羽流等离子体参数诊断,大连中国电推进会议,2006.10
[29]乔彩霞,空心阴极性能改进,大连中国电推进会议,2006.10
[30]陈琳英等,氙离子推力器放电室等离子体参数测量,真空与低温,第10卷第1期,2004.3
[31]王正,施晨毅,SPT等离子体诊断装置的考虑,上海航天局第801研究所内部资料,2002.11
[32]康小录,《霍尔电推进系统应用与集成技术》,总装课题总结报告,上海航天局801所内部资料,2005年12月
[33]施晨毅,校准型Faraday探针性能试验报告,上海航天局801所内部资料,2006.12
[34]Hofer R.R.,A Comparison of Nude and Collimated Faraday Probe for Use with Hall Thruster,IEPC-01-020
[35]Sang.Wook.Kim,Experimental Investegation of Plasma Parameter and Species-Dependent Ion Energy Distribution in the Plasma Exhaust Plume of hall Thrustr,Philosophy Thesis 1999
[36]Sankovic J.M.,Hamley J.A.,Haag T.W.,Performance Evaluation of the Russian SPT-100 Thruster at NASA LeRC,IEPC-93-094
[37]Garner,C.E.,Brophy,J.R.,Polk,J.E.,Pless,L.C.,A5,730-Hr Cyclic Endurance Test of the SPT-100,AIAA-95-2667,31st Joint Propulsion Conference,SanDiego,CA,July 10-12,1995.
[38]Hargus W.Jr.,Fife J.M.,Mason L.,Jankovsky,R.,Haag T.,Pinero L.,Snyder J.S.,Preliminary Performance Result for the High Performance Hall System SPT-140,AIAA-2000-3250
[39]Fife J.M.,Hargus W.Jr.,Jaworske,D.A.,Sarmient C.,Mason L.,Jankovsky,R.,Jankovsky R.,Snyder J.S.,Malone S.,Haas J.,Gallimore A.,Spacecraft Interaction Test Results of the High Performance Hall System SPY-140,AIAA-2000-3521
[40]Mason L.S.,Jankovsky,R.S.,Manzella D.H.,1000 Hours of Testing on a 10Kilowatt Hall Effect Thruster,AIAA-2001-3773
[41]Randolph Y.,Kim V.,Kaufman H.,Kozubsky K.,Zhurin V.,Day M.,Facility Effects on Stationary Plasma Thruster Testing,IEPC-93-93
[42]Hofer R.R.,Peterson P.Y.,Gallimore A.D.,Characterizing Vaccum Facility Backpressure Effects on the Performance of a Hall Thruster,IEPC-01-045
[43]Manzalla D.H.,Sankovic J.M.,Hall Thruster Ion Beam Characterization,AIAA-95-2927
[44]Haas J.M.,Low-Perturbation Interrogation of the Internal and Near-field Plasma Structure of a Hall Thruster Using a High-Speed Probe Positioning System,Ph.D thesis,Dept.of Aerospace Engineering,University of Michigan,pp.176-186,Feb.,2001
[45]De Grys K.H.,Tilley D.L.,Aadlang R.S.,BPT Hall Thruster Plume Characteristics,AIAA-99-2283
[46]Hofer R.R.,Peterson P.Y.,Gallimore A.D.,A High Apecific Impulse Ywo-Satge Hall Thruster with Plasma Lens Focusing,IEPC-01-036
[47]Pullins S.,Dressler R.A.,Chiu Y.H.,LevandierD.J.,Ion Dynamics in Hall Effect and Ion Thrusters:Xe++ XeSymmetric Charge Transfer,AIAA-2000-1647
[48]C.Perot,N.Gascon,Characterization Of A Laboratory Hall Thruster With Electrical Probes And Comparisons With A 2d Hybrid Pic-Mcc Model,AIAA-99-2716
[49]John Fife,Characterization of the SPT-100 Plume Using Electrostatic Probes
[50]Kang Xiaolu,Overview of Chinese Electric Propulsion Activities,IEPC-2001Pasadena,USA,Oct.2001
[2]施晨毅,康小录,霍尔推力器的发展与设计,上海航天,2007.12
[3]施晨毅,康小录,霍尔推力器的空间应用,上海航天2007.12
[4]魏延明,电推进技术的发展研究,航天工业总公司第502研究所,1999
[5]康小录,霍尔电推进系统应用分析,上海航天局第801研究所内部资料,2002.4
[6]康小录,“空间电推进技术研究”课题技术总结,中国国防科学技术报告,2002.10
[7]Oleson S.,Myers R.,Kluever C.,Riehl J.,Curran F.,Advanced Propulsion for Geostationary Orbit Insertion and North-South Station Keeping,AIAA-95-2513
[8]Gulezinski F.S.,Spores R.A.,Analysis of Hall-Effect Thrusters and Ion Engines for Orbit Transfer Mission,AIAA-96-2973
[9]G.Saccoccia,Electric Propulsion in Europe:Current Developments and Missons,AIAA-98-3177
[10]R.M.Myers,R.J.Cassady,Overview of Major U.S.Industrial Programs in Electric Propulsion,AIAA-98-3179
[11]Rodney L.Burton,Overview of US Academic Programs in Electric Propulsion,AIAA-98-3182
[12]Frank Stanley,Examination of The Structure and Evolution of Ion Energy Properties of a 5 kW Class Laboratory Hall Effect Thruster at Various Operational Conditions,a Doctoral Dissertation of The University of Michigan,1999
[13]廖宏图,稳态等离子体推力器理论研究,中国国防科学技术报告,2001.3
[14]James Matthew,Low-Perturbation Interrogation of The Internal and Near Field Plasma Structure of a Hall Thruster Using a High Speed Probe Positioning System,a doctoral dissertation of the university of Michigan,2001
[15]Hutchinson I.,Principles of Plasma Diagonostics,Cambridge University Press,New York 1987
[16]Jankovsky,R.S.,Jacobson D.T.,Mason L.S.,Rawlin V.K.,Mantenieks,M.A.,Manzella D.H.,Hofer R.R.,Peterson P.Y.,NASA's Hall Thruster Program,AIAA-2001-3888
[17]R.Joseph Cassady,Overview of Major US Industrial Programs in Electric Propulsion,AIAA 2001-3226,July 2001;
[18]R.A.Spores,Overview of the USAF Electric Propulsion Program,AIAA 2001-3225,July 2001;
[19]G.Saccoccia,Overview of European Electric Propulsion Activities,AIAA 2001-3228,July 2001;
[20]O.A.Gorshkov,Overview of Russian Activities in Electric Propulsion,AIAA 2001-3229,July 2001;
[21]J.Dunning,NASA's Electric Propulsion Program:Technology Investments for the New Millenium,AIAA 2001-3224,July 2001.
[22]Alec D.Gallimore,Review of the EP Activities of US Academia Compiled and Edited,AIAA-2001-3227;
[23]王正,HET性能实验报告,上海航天局第801研究所内部资料,2003
[24]饶雨生,等离子体物理基础,西安交通大学出版社,2000[30]
[25]甄汉生,等离子体加工技术,清华出版社,1992
[26]王正,HET性能优化设计报告,上海航天局第801研究所内部资料,2003
[27]王正,廖宏图,康小录,稳态等离子体(SPT)束流及等离子体诊断装置的研制和应用,总装2002推进会议
[28]余水林,Hall推力器羽流等离子体参数诊断,大连中国电推进会议,2006.10
[29]乔彩霞,空心阴极性能改进,大连中国电推进会议,2006.10
[30]陈琳英等,氙离子推力器放电室等离子体参数测量,真空与低温,第10卷第1期,2004.3
[31]王正,施晨毅,SPT等离子体诊断装置的考虑,上海航天局第801研究所内部资料,2002.11
[32]康小录,《霍尔电推进系统应用与集成技术》,总装课题总结报告,上海航天局801所内部资料,2005年12月
[33]施晨毅,校准型Faraday探针性能试验报告,上海航天局801所内部资料,2006.12
[34]Hofer R.R.,A Comparison of Nude and Collimated Faraday Probe for Use with Hall Thruster,IEPC-01-020
[35]Sang.Wook.Kim,Experimental Investegation of Plasma Parameter and Species-Dependent Ion Energy Distribution in the Plasma Exhaust Plume of hall Thrustr,Philosophy Thesis 1999
[36]Sankovic J.M.,Hamley J.A.,Haag T.W.,Performance Evaluation of the Russian SPT-100 Thruster at NASA LeRC,IEPC-93-094
[37]Garner,C.E.,Brophy,J.R.,Polk,J.E.,Pless,L.C.,A5,730-Hr Cyclic Endurance Test of the SPT-100,AIAA-95-2667,31st Joint Propulsion Conference,SanDiego,CA,July 10-12,1995.
[38]Hargus W.Jr.,Fife J.M.,Mason L.,Jankovsky,R.,Haag T.,Pinero L.,Snyder J.S.,Preliminary Performance Result for the High Performance Hall System SPT-140,AIAA-2000-3250
[39]Fife J.M.,Hargus W.Jr.,Jaworske,D.A.,Sarmient C.,Mason L.,Jankovsky,R.,Jankovsky R.,Snyder J.S.,Malone S.,Haas J.,Gallimore A.,Spacecraft Interaction Test Results of the High Performance Hall System SPY-140,AIAA-2000-3521
[40]Mason L.S.,Jankovsky,R.S.,Manzella D.H.,1000 Hours of Testing on a 10Kilowatt Hall Effect Thruster,AIAA-2001-3773
[41]Randolph Y.,Kim V.,Kaufman H.,Kozubsky K.,Zhurin V.,Day M.,Facility Effects on Stationary Plasma Thruster Testing,IEPC-93-93
[42]Hofer R.R.,Peterson P.Y.,Gallimore A.D.,Characterizing Vaccum Facility Backpressure Effects on the Performance of a Hall Thruster,IEPC-01-045
[43]Manzalla D.H.,Sankovic J.M.,Hall Thruster Ion Beam Characterization,AIAA-95-2927
[44]Haas J.M.,Low-Perturbation Interrogation of the Internal and Near-field Plasma Structure of a Hall Thruster Using a High-Speed Probe Positioning System,Ph.D thesis,Dept.of Aerospace Engineering,University of Michigan,pp.176-186,Feb.,2001
[45]De Grys K.H.,Tilley D.L.,Aadlang R.S.,BPT Hall Thruster Plume Characteristics,AIAA-99-2283
[46]Hofer R.R.,Peterson P.Y.,Gallimore A.D.,A High Apecific Impulse Ywo-Satge Hall Thruster with Plasma Lens Focusing,IEPC-01-036
[47]Pullins S.,Dressler R.A.,Chiu Y.H.,LevandierD.J.,Ion Dynamics in Hall Effect and Ion Thrusters:Xe++ XeSymmetric Charge Transfer,AIAA-2000-1647
[48]C.Perot,N.Gascon,Characterization Of A Laboratory Hall Thruster With Electrical Probes And Comparisons With A 2d Hybrid Pic-Mcc Model,AIAA-99-2716
[49]John Fife,Characterization of the SPT-100 Plume Using Electrostatic Probes
[50]Kang Xiaolu,Overview of Chinese Electric Propulsion Activities,IEPC-2001Pasadena,USA,Oct.2001
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