基于等效磁路的LIPS-200离子推力器磁场特性
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摘要
以放电室阳极振荡电压和放电损耗的最小化为目标,结合正交试验方法,获得了性能提升后可实现长期稳定工作的LIPS-200离子推力器最佳磁路结构与磁场构型。基于此,运用等效磁路方法,采用有限元离散形式,建立了LIPS-200离子推力器放电室磁场模型,研究了特定空间排布下电磁体的永磁体替代方案。利用放电室磁感应强度测试和整机工作性能对比验证了永磁体替代方案的等效性及分析方法的可行性和计算结果的正确性。结果表明:两种磁场状态下的推力器放电室特征位置磁感应强度相对误差低于5%,且推力器工作敏感参数变化情况符合预期,满足磁路等效目标,达到磁路结构再优化,工作性能再提升的整体目标。
The magnetic circuit structure and magnetic field configuration of LIPS-200 ion thruster capable of working steadily after performance enhancement were obtained to minimize the anode shock voltage and discharge loss by using orthogonal experimental method.Combined with the equivalent magnetic circuit method and the finite element discretization form,the magnetic field model of LIPS-200 ion thruster was established.Then the permanent magnet alternative proposals for electromagnet in specific spatial arrangements were studied.And the equivalence of alternative proposals and the effectiveness and feasibility of the simulation method were validated by comparing with the magnetic induction intensity and working performance.Results showed that the relative error of magnetic induction intensity in key points was less than 5%after magnetic field conversion,and the sensitive parameters changed in line with expectations,the design goal of magnetic circuit structure optimization and performance improvement for LIPS-200 ion thruster was well realized.
The magnetic circuit structure and magnetic field configuration of LIPS-200 ion thruster capable of working steadily after performance enhancement were obtained to minimize the anode shock voltage and discharge loss by using orthogonal experimental method.Combined with the equivalent magnetic circuit method and the finite element discretization form,the magnetic field model of LIPS-200 ion thruster was established.Then the permanent magnet alternative proposals for electromagnet in specific spatial arrangements were studied.And the equivalence of alternative proposals and the effectiveness and feasibility of the simulation method were validated by comparing with the magnetic induction intensity and working performance.Results showed that the relative error of magnetic induction intensity in key points was less than 5%after magnetic field conversion,and the sensitive parameters changed in line with expectations,the design goal of magnetic circuit structure optimization and performance improvement for LIPS-200 ion thruster was well realized.
引文
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[2]胡竟,王亮,张天平,等.LIPS-300离子推力器环形会切磁场等效磁路分析研究[J].推进技术,2018,39(3):715-720.HU Jing,WANG Liang,ZHANG Tianping,et al.Research on equivalent magnetic circuit of ring-cusp magnet field for LIPS-300ion thruster[J].Journal of Propulsion Technology,2018,39(3):715-720.(in Chinese)
[3]孔令轩,顾左,郭德洲,等.离子推力器阳极工质分配方式优化[J].航空动力学报,2017,32(3):756-761.KONG Lingxuan,GU Zuo,GUO Dezhou,et al.Optimization of anode propellant allocation on xenon ion thruster[J].Journal of Aerospace Power,2017,32(3):756-761.(in Chinese)
[4]孔令轩,顾左,郭德洲,等.氙离子推力器束流双荷离子特性及诊断[J].航空动力学报,2017,32(4):970-975.KONG Lingxuan,GU Zuo,GUO Dezhou,et al.Characterization and measurement of doubly charged ions in xenon ion thruster beam[J].Journal of Aerospace Power,2017,32(4):970-975.(in Chinese)
[5]李军星,张勇波,王治华,等.基于加速栅溅射腐蚀失效的离子推力器寿命预测[J].航空动力学报,2016,31(5):1047-1052.LI Junxing,ZHANG Yongbo,WANG Zhihua,et al.Life prediction of ion thruster based on sputtering erosion failure of accelerator grid[J].Journal of Aerospace Power,2016,31(5):1047-1052.(in Chinese)
[6]李军星,张勇波,傅惠民,等.离子推力器极少数据可靠性评估方法[J].航空动力学报,2015,30(10):2352-2356.LI Junxing,ZHANG Yongbo,FU Huimin,et al.Reliability evaluation method of ion thruster with very few failure data[J].Journal of Aerospace Power,2015,30(10):2352-2356.(in Chinese)
[7]ZHANG Tianping,WANG Xiaoyong,JIANG Haocheng.Initial flight test results of the LIPS-200electric propulsion system on SJ-9Asatellite[R].Kobe,Japan:34th International Electric Propulsion Conference IEPC 2015-47,2015.
[8]ZHANG Tianping.The LIPS-200ion electric propulsion system development for the DFH-3B satellite platform[R].Beijing:63rd International Astronautical Congress IAC13-C4.4.10,2013.
[9]ZHANG Tianping,YANG Le,TIAN Licheng,et al.The electric propulsion progress in LIP-2015[R].Kobe,Japan:34th International Electric Propulsion Conference IEPC2015-31,2015.
[10]胡竟,唐福俊,张天平,等.20cm氙离子推力器磁场优化与试验研究[J].科学技术与工程,2017,17(22):143-147.HU Jing,TANG Fujun,ZHANG Tianping,et al.Magnetic field optimization and experimental study of 20cm xenon ion thruster[J].Science Technology and Engineering,2017,17(22):143-147.(in Chinese)
[11]JOSE G D A.European Space Agency(ESA)electric propulsion activities[R].Kobe,Japan:34th International Electric Propulsion Conference IEPC 2015-02,2015.
[12]WILLIAM G T,KUEI R C,EZEQUIEL S,et al.Performance evaluation of the XIPS 25-cm thruster for application to NASA discovery missions[R].AIAA-2006-4666,2006.
[13]DAN M G,JAMES E P,IZABELA S,et al.Evaluation of25cm XIPS thruster life for deep space mission applications[R].Ann Arbor,US:31st International Electric Propulsion Conference IEPC-2009-152,2009.
[14]POLK J E,KAKUDA R Y,ANDERSON J R,et al.Performance of the NSTAR ion propulsion system on the deep space one mission[R].AIAA-2001-0965,2001.
[15]DANIEL A H,ALEC D G.Discharge chamber plasma structure of a 30cm NSTAR-type ion engine[R].AIAA-2004-3794,2004.
[16]CHARLES E G,ANITA S,JAMES G K.An evaluation of the discharge chamber of the 30,000hr life test of the deep space 1flight spare ion engine[R].AIAA-2004-3609,2004.
[17]SCOTT W B,MICHAEL J P.Development status of NEXT:NASA'S evolutionary xenon thruster[R].Toulouse,France:28th International Electric Propulsion Conference IEPC 2003-0288,2003.
[18]MICHAEL J P,SCOTT W B B.NEXT ion propulsion system development status and performance[R].AIAA-2007-5199,2007.
[19]DAN M G,RICHARD E W,IRA K.Analytical ion thruster discharge performance model[R].AIAA-2006-4486,2006.
[20]林其壬,赵佑民.磁路设计原理[M].北京:机械工业出版社,1987.
[21]ZHANG Zhexu,SONG Xiaoyan,QIAO Yinkai,et al.A nanocrystalline Sm-Co compound for high-temperature permanent magnets[J].Nanoscale,2013,5(6):2279-2284.
[22]CHEN C,WALMER M H,LIU S.Thermal stability and the effectiveness of coatings for Sm-Co 2:17high-temperature magnets at temperatures up to 550℃[J].IEEE Transactions on Magnetics,2004,40(4):2928-2930.