LHT-100霍尔电推进系统集成测试研究
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摘要
为了验证LHT-100霍尔电推进系统工作匹配性和工作性能,对霍尔电推进系统进行了集成测试研究,霍尔电推进系统包括霍尔推力器、电源处理单元、滤波单元、贮供单元和控制单元,对真空状态下的系统集成点火测试数据与设计指标的符合性进行了分析,研究表明:LHT-100霍尔电推进系统工作兼容性良好,系统集成拉偏后及系统宽功率范围工作正常稳定,各项性能指标满足要求,系统压力控制精度、阳极热节流器及阴极热节流器温度控制精度分别为±1.7%、±1.6%及±1.5%,系统推力83m N,比冲1600s,功率1536W,总效率48.2%,束流发散半角36.2°。
In order to verify the operation characteristics of LHT-100 Hall Electric propulsion,study on integrated test of Hall electric propulsion was carried out. Hall electric propulsion system includes Hall thruster,power processing unit,filter unit,propellant storage and feeding unit,digital and interface control unit. The results of the integrated test program of Hall electric propulsion system under vacuum,including relevant test data and design features,will be discussed. The study shows that there are of good work compatibility for LHT-100 Hall electric propulsion system. The system works stably after down-deflection and over a wide power range. All kinds of performance index of the system met the design requirements. The system pressure control precision,anode and cathode throttle temperature control accuracy were ±1.7%,±1.6% and ±1.5%,respectively. The system thrust is 83 m N,specific impulse is 1600 s,power is 1536 W,total efficiency is 48.2%,beam divergence half angle is 36.2°.
In order to verify the operation characteristics of LHT-100 Hall Electric propulsion,study on integrated test of Hall electric propulsion was carried out. Hall electric propulsion system includes Hall thruster,power processing unit,filter unit,propellant storage and feeding unit,digital and interface control unit. The results of the integrated test program of Hall electric propulsion system under vacuum,including relevant test data and design features,will be discussed. The study shows that there are of good work compatibility for LHT-100 Hall electric propulsion system. The system works stably after down-deflection and over a wide power range. All kinds of performance index of the system met the design requirements. The system pressure control precision,anode and cathode throttle temperature control accuracy were ±1.7%,±1.6% and ±1.5%,respectively. The system thrust is 83 m N,specific impulse is 1600 s,power is 1536 W,total efficiency is 48.2%,beam divergence half angle is 36.2°.
引文
[1]Manzella D,Jankovsky R,Elliott F,et al.Hall Thruster Plume Measurements on-Board the Russian Express Satellites[R].NASA/TM-2001-211217.
[2]Sitnikova N,Volkov D,Maximov I,et al.Hall Effect Thruster Interactions Data from the Russian Express-A2and Express-A3 Satellites[R].NASA/CR-2003-212005.
[3]张天平,唐福俊,田华兵,等.电推进航天器的特殊环境及其影响[J].航天器环境工程,2007,24(2):88-94.
[4]张郁.电推进技术的研究应用现状及其发展趋势[J].火箭推进,2005,31(2):27-36.
[5]Colbert T S,Day M,Fischer G,et al.Plan and Status of the Development and Qualification Program for Stationary Plasma Thruster[C].Monterey:Joint Propulsion Conference and Exhibit,1993.
[6]田立成,龙建飞,郭宁,等.卫星敏感区域霍尔推力器束流沉积污染模型[J].真空科学与技术学报,2013,33(9):883-887.
[7]田立成,郭宁,龙建飞,等.LHT-100霍尔推力器宽功率范围工作实验研究[J].推进技术,2014,35(9):1283-1289.(TIAN Li-cheng,GUO Ning,LONG Jian-fei,et al.Experimental Study of LHT-100 Hall Thruster Operation in the Wide Power Range[J].Journal of Propulsion Technology,2014,35(9):1283-1289.)
[8]Bugrova A I.Physical Processes and Characteristics of Stationary Plasma Thrusters with Closed Electron Drift[C].Viareggio:22nd International Electric Propulsion Conference,1991.
[9]John R Brophy,et al.Performance of the Stationary Plasma Thruster:SPT-100[R].AIAA 92-3155.
[10]Absalamov S K.Measurement of Plasma Parameters in the Stationary Plasma Thruster(SPT-100)Plume and its Effect on Spacecraft Components[R].AIAA 92-3156.
[11]Charles E Garner.Performance Evaluation and Life Testing of the SPT-100[C].Seattle:23rd International Electric Propulsion Conference,1993.
[12]Sekerak M J,Longmier B W,Gallimore A D,et al.Azimuthal Spoke Propagation in Hall Effect Thrusters[J].IEEE Transactions on Plasma Science,2015,43(1):72-85.
[13]Lazurenko A,Vial V,Bouchoule A,et al.Dual-Mode Operation of Stationary Plasma Thrusters[J].Journal of Propulsion and Power,2015,22(1):38-475.
[14]Kim V.Main Physical Features and Processes Determining the Performance of Stationary Plasma Thrusters[J].Journal of Propulsion and Power,2015,14(5):736-743.
[15]Arhipov B A,Krochak L Z,Kudriavcev S S,et al.In-vestigation of the Stationary Plasma Thruster(SPT-100)-Characteristics and Thermal Maps at the Raised Discharge Power[R].AIAA 1998-3791.
[16]David Manzella,David Jacobson.Investigation of LowVoltage/High-Thrust Hall Thruster Operation[R].AIAA 2003-5004.
[17]Day M,Maslennikov N,Randolph T,et al.SPT-100Subsystem Qualification Status[R].AIAA 96-2713.
[18]Lyszyk M,Klinger E,Secheresse O,et al.PPS 1350Plasma Thruster Qualification Status[C].Amsterdam:50th International Astronautical Congress,1999.
[19]Hobbs G D,Wesson J A.Heat Flow Through a Langmuir Sheath in the Presence of Electron Emission[J].Plasma Physics,1966,9(1):85-87.
[20]田立成,高俊,李兴坤,等.LHT-100自励磁霍尔推力器热特性测试和热真空实验研究[J].推进技术,2016,37(4):793-800.(TIAN Li-cheng,GAO Jun,LI Xing-kun,et al.Experimental Study of Thermal Characteristics and Thermal Vacuum of LHT-100Self-Excited Hall Thruster[J].Journal of Propulsion Technology,2016,37(4):793-800.)
[21]田立成,石红,李娟,等.二次电子发射对稳态等离子体推进器加速通道鞘层的影响[J].固体火箭技术,2012,35(2):193-197.
[22]赵成仁,顾左,田立成,等.LHT-100霍尔推力器滤波设计与放电震荡关系研究[J].真空,2015,52(1):63-66.
[23]田立成,赵成仁,孙小菁.电推进器在GEO静止卫星上的安装策略[J].真空,2014,51(2):70-73.
[24]田立成,郭宁,顾左,等.超大型航天器应用电推进系统方案设计[J].真空,2014,51(5):68-73.
[2]Sitnikova N,Volkov D,Maximov I,et al.Hall Effect Thruster Interactions Data from the Russian Express-A2and Express-A3 Satellites[R].NASA/CR-2003-212005.
[3]张天平,唐福俊,田华兵,等.电推进航天器的特殊环境及其影响[J].航天器环境工程,2007,24(2):88-94.
[4]张郁.电推进技术的研究应用现状及其发展趋势[J].火箭推进,2005,31(2):27-36.
[5]Colbert T S,Day M,Fischer G,et al.Plan and Status of the Development and Qualification Program for Stationary Plasma Thruster[C].Monterey:Joint Propulsion Conference and Exhibit,1993.
[6]田立成,龙建飞,郭宁,等.卫星敏感区域霍尔推力器束流沉积污染模型[J].真空科学与技术学报,2013,33(9):883-887.
[7]田立成,郭宁,龙建飞,等.LHT-100霍尔推力器宽功率范围工作实验研究[J].推进技术,2014,35(9):1283-1289.(TIAN Li-cheng,GUO Ning,LONG Jian-fei,et al.Experimental Study of LHT-100 Hall Thruster Operation in the Wide Power Range[J].Journal of Propulsion Technology,2014,35(9):1283-1289.)
[8]Bugrova A I.Physical Processes and Characteristics of Stationary Plasma Thrusters with Closed Electron Drift[C].Viareggio:22nd International Electric Propulsion Conference,1991.
[9]John R Brophy,et al.Performance of the Stationary Plasma Thruster:SPT-100[R].AIAA 92-3155.
[10]Absalamov S K.Measurement of Plasma Parameters in the Stationary Plasma Thruster(SPT-100)Plume and its Effect on Spacecraft Components[R].AIAA 92-3156.
[11]Charles E Garner.Performance Evaluation and Life Testing of the SPT-100[C].Seattle:23rd International Electric Propulsion Conference,1993.
[12]Sekerak M J,Longmier B W,Gallimore A D,et al.Azimuthal Spoke Propagation in Hall Effect Thrusters[J].IEEE Transactions on Plasma Science,2015,43(1):72-85.
[13]Lazurenko A,Vial V,Bouchoule A,et al.Dual-Mode Operation of Stationary Plasma Thrusters[J].Journal of Propulsion and Power,2015,22(1):38-475.
[14]Kim V.Main Physical Features and Processes Determining the Performance of Stationary Plasma Thrusters[J].Journal of Propulsion and Power,2015,14(5):736-743.
[15]Arhipov B A,Krochak L Z,Kudriavcev S S,et al.In-vestigation of the Stationary Plasma Thruster(SPT-100)-Characteristics and Thermal Maps at the Raised Discharge Power[R].AIAA 1998-3791.
[16]David Manzella,David Jacobson.Investigation of LowVoltage/High-Thrust Hall Thruster Operation[R].AIAA 2003-5004.
[17]Day M,Maslennikov N,Randolph T,et al.SPT-100Subsystem Qualification Status[R].AIAA 96-2713.
[18]Lyszyk M,Klinger E,Secheresse O,et al.PPS 1350Plasma Thruster Qualification Status[C].Amsterdam:50th International Astronautical Congress,1999.
[19]Hobbs G D,Wesson J A.Heat Flow Through a Langmuir Sheath in the Presence of Electron Emission[J].Plasma Physics,1966,9(1):85-87.
[20]田立成,高俊,李兴坤,等.LHT-100自励磁霍尔推力器热特性测试和热真空实验研究[J].推进技术,2016,37(4):793-800.(TIAN Li-cheng,GAO Jun,LI Xing-kun,et al.Experimental Study of Thermal Characteristics and Thermal Vacuum of LHT-100Self-Excited Hall Thruster[J].Journal of Propulsion Technology,2016,37(4):793-800.)
[21]田立成,石红,李娟,等.二次电子发射对稳态等离子体推进器加速通道鞘层的影响[J].固体火箭技术,2012,35(2):193-197.
[22]赵成仁,顾左,田立成,等.LHT-100霍尔推力器滤波设计与放电震荡关系研究[J].真空,2015,52(1):63-66.
[23]田立成,赵成仁,孙小菁.电推进器在GEO静止卫星上的安装策略[J].真空,2014,51(2):70-73.
[24]田立成,郭宁,顾左,等.超大型航天器应用电推进系统方案设计[J].真空,2014,51(5):68-73.