附加场强度对低工况AF-MPDT性能的影响
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摘要
附加磁场强度与位形是大功率磁等离子体动力推力器(Applied Field Magnetoplasmadynamic Thruster, AF-MPDT)重要工作参数之一。为验证附加磁场强度对低工况下AF-MPDT性能的影响,采用北京控制工程研究所联合北京航空航天大学研制的100 kW级AF-MPDT原理样机,利用推力靶测量系统进行高温震动环境下的推力测量,针对不同附加磁场强度(30～230 mT)下的推力器开展中低功率性能研究实验。实验结果表明,在一定范围内,增加磁场强度可提升低工况下推力器推力、比冲、放电电压及效率等性能指标,并且放电电流越大,性能提升效果越明显。分析表明,低工况下AF-MPDT推力、比冲与磁场强度的平方根呈线性关系;推力器放电电压与磁场强度呈线性关系;推力器效率随磁场强度增强而增加,最终达到相应工况下的极限。
Intensity and profile of applied magnetic field are working parameters of great significance for the applied field magnetoplasmadynamic thruster(AF-MPDT).A 100 kW AF-MPDT principle prototype developed by Beijing Institute of Control Engineering and Beihang University was used to estimate the performance of MPDT under medium power with applied magnetic field varied from 30 mT to 230 mT.A target thrust measurement method under high temperature and vibrating environment was applied.The test results show that within a certain range,increasing the intensity of applied magnetic field could improve the thrust,impulse,discharge voltage and efficiency of AF-MPDT under low power.Besides, the performance improvement of AF-MPDT is more obviouse under higher discharge current.Further analysis shows that when the AF-MPDT was operated under low power, thrust and impulse are proportional to the square root for intensity of magnetic field; discharge voltage is proportional to intensity of magnetic field; efficiency increases with intensity of magnetic field but finally reaches the up limit under the corresponding working condition.
Intensity and profile of applied magnetic field are working parameters of great significance for the applied field magnetoplasmadynamic thruster(AF-MPDT).A 100 kW AF-MPDT principle prototype developed by Beijing Institute of Control Engineering and Beihang University was used to estimate the performance of MPDT under medium power with applied magnetic field varied from 30 mT to 230 mT.A target thrust measurement method under high temperature and vibrating environment was applied.The test results show that within a certain range,increasing the intensity of applied magnetic field could improve the thrust,impulse,discharge voltage and efficiency of AF-MPDT under low power.Besides, the performance improvement of AF-MPDT is more obviouse under higher discharge current.Further analysis shows that when the AF-MPDT was operated under low power, thrust and impulse are proportional to the square root for intensity of magnetic field; discharge voltage is proportional to intensity of magnetic field; efficiency increases with intensity of magnetic field but finally reaches the up limit under the corresponding working condition.
引文
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[16] ALBERTONI R,PAGANUCCI F,ANDR ENUCCI M.A phenomenological performance model for applied-field MPD thrusters[J].Acta astronautica,2015,107:177 -186.
[17] LEV D R,CHOUEIRI E.Scaling of efficiency with applied magnetic field in magnetoplasmadynamic thrusters[J].Journal and Power,2012,28(3):609-616.
[18] LI Zefeng,TANG Haibin,WANG Yibai,et al.Increasing the effective voltage in applied-field MPD thrusters[J].Journal of Physics,2018,51 (8).
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[20] 张岩,康小录,乔彩霞.钡钨空心阴极放电等离子体特性实验研究[J].火箭推进,2014,40(5):55-60.ZHANG Yan,KANG Xiaolu,QIAO Caixia.Experimental investigation for discharge plasma properties of BaW hollow cathode[J].Journal of Rocket Propulsion,2014,40(5):55-60.
[21] BARNETT J W,JAHN R G.Onset phenomena in MPD thrusters[C]//AIAA/DGLR/JSASS 18th International Electric Propulsion Conference.Virginia:AIAA,1985.
[2] SASOH A.Simple formulation of magnetoplasma-dynamic acceleration[J].Physics of Plasmas,1994,1 (3):464-469.
[3] COLETTI M.A thrust formula for an MPD thruster with applied-magetic field [J].Acta Astronautic,2012,81(2):667-674.
[4] ERSOHN F H,GIRIMAJI S S,STAACK D,et al.Magnetic nozzle plasma plume:review of crucial physical phenomena[C]//48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Atlanta:AIAA,2012.
[5] BOXBERGER A,BAMBACH P,HERDRICH G,et al.Experimental investigation of steady-state applied-field magnetoplasmadynamic thrusters at institute of space system[C] //48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Atlanta:AIAA,2012.
[6] BOXBERGER A J,STEL P,HERIDRICH G.Performance of 100kW steady state applied-field MPD thruster[C]//31st International Symposium on Space Technology and Science.Japan:Matsuyama,2017.
[7] ALBERTONI R,PAGANUCCI F,ROSSETTI P,et al.Experimental study of a hundred-kilowatt class applied-field magnetoplasmadynamic thruster[J].Journal of Propulsion and Power,2013,29(5):1138-1145.
[8] SOVEY J S,MANTENIEKS M.Performance and lifetime assessment of magnetoplasmadynamic arc thruster[J].Journal of Propulsion and Power,1991,7(1):71-83.
[9] PATRICK R M,SCHNEIDEMAN A M.Performance characteristics of a magnetic annular arc[C]// 6th Symposium on Engineering Aspects of Magnetohydrodynamics.Pittsburgh:PA,1965.
[10] ARAKAWA Y,SASON A.Electromagnetic effects in an applied-field magnetoplasmadynamic thruster[J].Journal of Propulsion and Power,1992,8(1):98-102.
[11] TAHARA H,KAGAYA Y,YOSHIKAWAI T.Effects of applied magnetic fields on performance of quasisteady magnetoplasmadynamic arcjet[J].Journal of Propulsion and Power,1995,11(2):337-342.
[12] WANG B J,YANG W J,TANG H B,et al.Target thrust measurement for applied-field magneto-plasmadynamic thruster[J].Measurement Science and Technology,2018,29(7).
[13] 宁中喜,范金蕤.三丝扭摆微推力在线测量方法及不确定度分析[J].测控技术,2012,31(5):45-48.
[14] 杨涓,刘宪闯,王与权,等.微波推力器独立系统的三丝扭摆推力测量[J].推进技术,2016,37(2):362-371.
[15] MIKELLIDES P G,PRUCHI P J.Applied-field magnetoplasmadynamic thrusters,part 2:analytic expressions for thrust and voltage[J].Journal of Propulsion and Power,2000,16(5):894-901.
[16] ALBERTONI R,PAGANUCCI F,ANDR ENUCCI M.A phenomenological performance model for applied-field MPD thrusters[J].Acta astronautica,2015,107:177 -186.
[17] LEV D R,CHOUEIRI E.Scaling of efficiency with applied magnetic field in magnetoplasmadynamic thrusters[J].Journal and Power,2012,28(3):609-616.
[18] LI Zefeng,TANG Haibin,WANG Yibai,et al.Increasing the effective voltage in applied-field MPD thrusters[J].Journal of Physics,2018,51 (8).
[19] MYERS R M ,SOULAS G C.Anode power deposition in applied-field MPD thrusters[C] //28th Joint Propulsion Conference.Nashville:AIAA,1992.
[20] 张岩,康小录,乔彩霞.钡钨空心阴极放电等离子体特性实验研究[J].火箭推进,2014,40(5):55-60.ZHANG Yan,KANG Xiaolu,QIAO Caixia.Experimental investigation for discharge plasma properties of BaW hollow cathode[J].Journal of Rocket Propulsion,2014,40(5):55-60.
[21] BARNETT J W,JAHN R G.Onset phenomena in MPD thrusters[C]//AIAA/DGLR/JSASS 18th International Electric Propulsion Conference.Virginia:AIAA,1985.