Experiment of Hall thruster plume effects on different ground experimental conditions
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摘要
Reducing the influence of back-sputtering effect can effectively improve the accuracy of the measurement of the Hall thruster plume effect.Quartz crystal microbalance(QCM)was used to measure the deposition and sputtering distribution of HET-40 thruster plume on two different experimental conditions:case1,using liquid nitrogen heat sinks and case 2,without using liquid nitrogen heat sinks.Meanwhile,X-ray photoelectron spectroscopy(XPS)was used to analyze the composition of the QCM surface after two experiments.The results of the two experiments showed that the sputtering rate under the condition of case 1 was slightly higher than case 2.Especially within the range of 90°to 110°relative to the thruster axis,case 1 experiment result showed sputtering effect,while case 2 experiment showed deposition effect.Through analysis of the experimental results,it can be found that using liquid nitrogen heat sink to reduce the temperature of the inner wall surface of vacuum chamber can effectively adsorb the particles sputtered by the plume and reduce the concentration of back-sputtering particles,leading to the above phenomenon.
Reducing the influence of back-sputtering effect can effectively improve the accuracy of the measurement of the Hall thruster plume effect.Quartz crystal microbalance(QCM)was used to measure the deposition and sputtering distribution of HET-40 thruster plume on two different experimental conditions:case1,using liquid nitrogen heat sinks and case 2,without using liquid nitrogen heat sinks.Meanwhile,X-ray photoelectron spectroscopy(XPS)was used to analyze the composition of the QCM surface after two experiments.The results of the two experiments showed that the sputtering rate under the condition of case 1 was slightly higher than case 2.Especially within the range of 90°to 110°relative to the thruster axis,case 1 experiment result showed sputtering effect,while case 2 experiment showed deposition effect.Through analysis of the experimental results,it can be found that using liquid nitrogen heat sink to reduce the temperature of the inner wall surface of vacuum chamber can effectively adsorb the particles sputtered by the plume and reduce the concentration of back-sputtering particles,leading to the above phenomenon.
Reducing the influence of back-sputtering effect can effectively improve the accuracy of the measurement of the Hall thruster plume effect.Quartz crystal microbalance(QCM)was used to measure the deposition and sputtering distribution of HET-40 thruster plume on two different experimental conditions:case1,using liquid nitrogen heat sinks and case 2,without using liquid nitrogen heat sinks.Meanwhile,X-ray photoelectron spectroscopy(XPS)was used to analyze the composition of the QCM surface after two experiments.The results of the two experiments showed that the sputtering rate under the condition of case 1 was slightly higher than case 2.Especially within the range of 90°to 110°relative to the thruster axis,case 1 experiment result showed sputtering effect,while case 2 experiment showed deposition effect.Through analysis of the experimental results,it can be found that using liquid nitrogen heat sink to reduce the temperature of the inner wall surface of vacuum chamber can effectively adsorb the particles sputtered by the plume and reduce the concentration of back-sputtering particles,leading to the above phenomenon.
引文
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[2]PIDGEON D J,COREY R L,SAUER B,et al.Two years on-orbit performance of SPT-100electric propulsion[R].AIAA-2006-5353,2006.
[3]HARGUS W A.Investigation of the plasma acceleration mechanism within a coaxial Hall thruster[D].San Francisco,US:Stanford University,2001.
[4]KING L B,GALLIMORE A D.Mass spectral measurements in the plume of an SPT-100Hall thruster[J].Journal of Propulsion and Power,2000,16(6):1086-1092.
[5]KING L B,GALLIMORE A D.Ion-energy diagnostics in an SPT-100plume from thrust axis to backflow[J].Journal of Propulsion and Power,2004,20(2):228-242.
[6]PENCIL E J,RANDOLPH T,MANZELLA D H.End-oflife stationary plasma thruster far-field plume characterization[R].AIAA 96-2709,1996.
[7]JAWORSKE D A.Hall effect thruster plume contamination and erosion study[R].NASA TM-2000-210204,2000.
[8]TREVISANI L,NEGRINI F,MARTINEZ-SANCHEZ M.Material deposition measurements from a Hall thruster using aquartz crystal microbalance[R].Chia Laguna,Sardinia,Italy:4th International Spacecraft Propulsion Conference,2004.
[9]KHARTOV S,EGOROV V,NADIRADZE A,et al.Angular distribution of ceramic isolator sputtered material in the SPT jet[R].Toulouse,France:30th International Electric Propulsion Conference,2003.
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[12]SCORTECCI F,BONELLI E,MICHELOZZI B,et al.Performance of a large vacuum facility for spacecraft propulsion testing[R].Chia Laguna,Sardinia,Italy:4th International Spacecraft Propulsion Conference,2004.
[13]SAVERDI M,SIGNORI M,MILANESCHI L,et al.The IV10space simulator for high power electric propulsion testing:performance improvements and operation status[R].Florence,Italy:30th International Electric Propulsion Conference,2007.
[14]YANG Zhe,CAI Guobiao,GU Zuo,et al.Ground simulation of contamination induced by plume of LIPS200ion thruster[J].Chinese Journal of Vacuum Science and Technology,2016,36(10):1156-1161.(in Chinese)
[15]WANG Wenlong,CAI Guobiao,ZHOU Jianping.Largescale vacuum vessel design and finite element analysis[J].Chinese Journal of Aeronautics,2012,25(2):189-197.
[16]LING Guilong,WANG Wenlong,CAI Guobiao,et al.Liquid helium heat sink design for experimental study ofengine's plume and vacuum effects[J].Journal of Aerospace Power,2011,26(11):2630-2635.(in Chinese)
[17]LING Guilong,CAI Guobiao,ZHANG Jianhua.Oil-free vacuum system design based on vacuum plume experiment[J].Journal of Aerospace Power,2013,28(5):1173-1179.(in Chinese)
[18]SHANG Shengfei,CAI Guobiao,ZHU Dingqiang,et al.Design of double-layer anti-sputtering targets for plume effects experimental system[J].Science China(Technological Sciences),2016,59(8):1265-1275.
[19]ABSALAMOV S,ANDREEV V,COLBERT T,et al.Measurement of plasma parameters in the stationary plasma thruster(SPT-100)plume and its effect on spacecraft components[R].AIAA 92-3156,1992.
[20]MANZELLA D H,SANKOVIC J M.Hall thruster ion beam characterization[R].AIAA 95-2927,1995.
[21]GALLIMORE A D,GILCHRIST B E,KING L B,et al.Plume characterization of the SPT-100[R].AIAA 96-3298,1996.
[22]WALKER M L,VICTOR A L,HOFER R R,et al.Effect of backpressure on ion current density measurements in hall thruster plumes[J].Journal of Propulsion and Power,2005,21(3):408-415.
[23]WALKER M L,HOFER R R,GALLIMORE A D.Ioncollection in Hall thruster plumes[J].Journal of Propulsion and Power,2006,22(1):205-209.
[24]DIAMANT K D,LIANG R,COREY R L.The effect of background pressure on spt-100hall thruster performance[R].AIAA-2014-3710,2014.
[25]SHIMIZU H,ONO M,NAKAYAMA K.Effect of target temperature on surface composition changes of Cu-Ni alloys during Ar ion bombardment[J].Journal of Applied Physics,1975,46(1):460-462.
[26]BESOCKE K,BERGER S,HOFER W O,et al.A search for a thermal spike effect in sputtering:Ⅰtemperature dependence of the yield at low-kev,heavy-ion bombardment[M].Passaic County,New Jersey,US:Humana Press,1982.
[27]FONG M C.General sticking coefficient theory for neutral and photochemically excited molecules[C]∥International Symposium on Optical Science,Engineering,and Instrumentation.San Diego,US:Surface Accommodation of Molecular Contaminants,1998:238-249.
[28]CHEN P T,HEDGELAND R J,THOMSON S R.Surface accommodation of molecular contaminants[C]∥34th Annual International Technical Symposium on Optical and Optoelectronic Applied Science and Engineering.San Diego,US:Surface Accommodation of Molecular Contaminants,1990:327-336.
[2]PIDGEON D J,COREY R L,SAUER B,et al.Two years on-orbit performance of SPT-100electric propulsion[R].AIAA-2006-5353,2006.
[3]HARGUS W A.Investigation of the plasma acceleration mechanism within a coaxial Hall thruster[D].San Francisco,US:Stanford University,2001.
[4]KING L B,GALLIMORE A D.Mass spectral measurements in the plume of an SPT-100Hall thruster[J].Journal of Propulsion and Power,2000,16(6):1086-1092.
[5]KING L B,GALLIMORE A D.Ion-energy diagnostics in an SPT-100plume from thrust axis to backflow[J].Journal of Propulsion and Power,2004,20(2):228-242.
[6]PENCIL E J,RANDOLPH T,MANZELLA D H.End-oflife stationary plasma thruster far-field plume characterization[R].AIAA 96-2709,1996.
[7]JAWORSKE D A.Hall effect thruster plume contamination and erosion study[R].NASA TM-2000-210204,2000.
[8]TREVISANI L,NEGRINI F,MARTINEZ-SANCHEZ M.Material deposition measurements from a Hall thruster using aquartz crystal microbalance[R].Chia Laguna,Sardinia,Italy:4th International Spacecraft Propulsion Conference,2004.
[9]KHARTOV S,EGOROV V,NADIRADZE A,et al.Angular distribution of ceramic isolator sputtered material in the SPT jet[R].Toulouse,France:30th International Electric Propulsion Conference,2003.
[10]BIAGIONI L,BOCCALETTO L,MARCUCCIO S,et al.A large space simulator for electric propulsion testing:design requirements and engineering analysis[R].AIAA-2000-3750,2000.
[11]BIAGIONI L,KIM V,NICOLINI D,et al.Basic issues in electric propulsion testing and the need for international standards[R].Toulouse,France:28th International Electric Propulsion Conference,2001.
[12]SCORTECCI F,BONELLI E,MICHELOZZI B,et al.Performance of a large vacuum facility for spacecraft propulsion testing[R].Chia Laguna,Sardinia,Italy:4th International Spacecraft Propulsion Conference,2004.
[13]SAVERDI M,SIGNORI M,MILANESCHI L,et al.The IV10space simulator for high power electric propulsion testing:performance improvements and operation status[R].Florence,Italy:30th International Electric Propulsion Conference,2007.
[14]YANG Zhe,CAI Guobiao,GU Zuo,et al.Ground simulation of contamination induced by plume of LIPS200ion thruster[J].Chinese Journal of Vacuum Science and Technology,2016,36(10):1156-1161.(in Chinese)
[15]WANG Wenlong,CAI Guobiao,ZHOU Jianping.Largescale vacuum vessel design and finite element analysis[J].Chinese Journal of Aeronautics,2012,25(2):189-197.
[16]LING Guilong,WANG Wenlong,CAI Guobiao,et al.Liquid helium heat sink design for experimental study ofengine's plume and vacuum effects[J].Journal of Aerospace Power,2011,26(11):2630-2635.(in Chinese)
[17]LING Guilong,CAI Guobiao,ZHANG Jianhua.Oil-free vacuum system design based on vacuum plume experiment[J].Journal of Aerospace Power,2013,28(5):1173-1179.(in Chinese)
[18]SHANG Shengfei,CAI Guobiao,ZHU Dingqiang,et al.Design of double-layer anti-sputtering targets for plume effects experimental system[J].Science China(Technological Sciences),2016,59(8):1265-1275.
[19]ABSALAMOV S,ANDREEV V,COLBERT T,et al.Measurement of plasma parameters in the stationary plasma thruster(SPT-100)plume and its effect on spacecraft components[R].AIAA 92-3156,1992.
[20]MANZELLA D H,SANKOVIC J M.Hall thruster ion beam characterization[R].AIAA 95-2927,1995.
[21]GALLIMORE A D,GILCHRIST B E,KING L B,et al.Plume characterization of the SPT-100[R].AIAA 96-3298,1996.
[22]WALKER M L,VICTOR A L,HOFER R R,et al.Effect of backpressure on ion current density measurements in hall thruster plumes[J].Journal of Propulsion and Power,2005,21(3):408-415.
[23]WALKER M L,HOFER R R,GALLIMORE A D.Ioncollection in Hall thruster plumes[J].Journal of Propulsion and Power,2006,22(1):205-209.
[24]DIAMANT K D,LIANG R,COREY R L.The effect of background pressure on spt-100hall thruster performance[R].AIAA-2014-3710,2014.
[25]SHIMIZU H,ONO M,NAKAYAMA K.Effect of target temperature on surface composition changes of Cu-Ni alloys during Ar ion bombardment[J].Journal of Applied Physics,1975,46(1):460-462.
[26]BESOCKE K,BERGER S,HOFER W O,et al.A search for a thermal spike effect in sputtering:Ⅰtemperature dependence of the yield at low-kev,heavy-ion bombardment[M].Passaic County,New Jersey,US:Humana Press,1982.
[27]FONG M C.General sticking coefficient theory for neutral and photochemically excited molecules[C]∥International Symposium on Optical Science,Engineering,and Instrumentation.San Diego,US:Surface Accommodation of Molecular Contaminants,1998:238-249.
[28]CHEN P T,HEDGELAND R J,THOMSON S R.Surface accommodation of molecular contaminants[C]∥34th Annual International Technical Symposium on Optical and Optoelectronic Applied Science and Engineering.San Diego,US:Surface Accommodation of Molecular Contaminants,1990:327-336.