霍尔推力器分割高偏压电极等离子体放电特性
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摘要
霍尔推力器通道等离子体与壁面有很强的相互作用,为了降低壁面腐蚀,提高在轨寿命,针对推力器全通道放电过程建立二维物理模型,采用粒子模拟方法(Particle-In-Cell),数值研究了电离区壁面分割高于阳极偏压的低发射石墨电极对推力器放电特性的影响,讨论了放电通道电势、离子数密度、电子温度、电离速率及比冲的变化规律。结果表明:在电离区不同位置分割高偏压电极对等离子体放电特性影响明显,电极位置在电离区前端时,电极偏压高于阳极电压60V时通道内放电等离子体参数几乎不变。而电极位置在电离区末端,电极偏压高于阳极电压18V时就会导致加速区轴向扩张,离子聚焦效果强,电子温度显著升高,电子与壁面相互作用减弱,羽流发散角减小。由此推力器比冲提升约12%,寿命延长,性能提高。
Hall thruster plasma has strong interactions with the channel wall.In order to reduce the surface corrosion and enhance the lifetime,a two-dimensional physical model was established based on the discharge process of Hall thruster,and a Particle-in-cell(PIC)simulation method was applied to study the influences of segmented low emissive graphite electrodes on discharge characteristics of the Hall thruster channel.The influences of biased segmented electrode arrangedin the ionization region on electric potential,ion number density,electron temperature,ionization rate,discharge current and impulse were discussed.The results show that segmentation of high biased electrodes at different positions in the ionization region has obvious influences on the plasma discharge characteristics.When the electrode position is in the front ionization region and the electrode bias voltage is 60 Vhigher than the anode,the plasma parameters of discharge channel are almost unchanged.When the electrode is at the end of the ionization region,and the electrode bias voltage is 18 Vhigher than the anode,the accelerating region expands axially,the ion velocity vectors are more focused,the electron temperature increases significantly which decreases the interaction between electrons and wall,and the divergence angle of the plume also reduces.The thruster specific impulse increases about 12%,the performance and lifetime of the thruster are improved.
Hall thruster plasma has strong interactions with the channel wall.In order to reduce the surface corrosion and enhance the lifetime,a two-dimensional physical model was established based on the discharge process of Hall thruster,and a Particle-in-cell(PIC)simulation method was applied to study the influences of segmented low emissive graphite electrodes on discharge characteristics of the Hall thruster channel.The influences of biased segmented electrode arrangedin the ionization region on electric potential,ion number density,electron temperature,ionization rate,discharge current and impulse were discussed.The results show that segmentation of high biased electrodes at different positions in the ionization region has obvious influences on the plasma discharge characteristics.When the electrode position is in the front ionization region and the electrode bias voltage is 60 Vhigher than the anode,the plasma parameters of discharge channel are almost unchanged.When the electrode is at the end of the ionization region,and the electrode bias voltage is 18 Vhigher than the anode,the accelerating region expands axially,the ion velocity vectors are more focused,the electron temperature increases significantly which decreases the interaction between electrons and wall,and the divergence angle of the plume also reduces.The thruster specific impulse increases about 12%,the performance and lifetime of the thruster are improved.
引文
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[9] XU K,WALKER M L R.Plumecharacterization of an ion-focusing Hall thruster[J].Journal of Propulsion&Power,2015,28(5):1105-1115.
[10]李青曼,王平阳,徐宗琦.金刚石对霍尔推力器通道壁面抗溅射性能的影响[J].中国空间科学技术,2017,37(6):62-67.LI Q M,WANG P Y,XU Z Q.Effect of diamond onsputtering resistance performance of Hall thruster channel wall[J].Chinese Space Science and Technology,2017,37(6):62-67(in Chinese).
[11]曹安宁.霍尔推力器通道壁面分割放电特性研究[D].大连:大连海事大学,2015.CAO A N.Research on the discharge characteristics of channel wall segmenting in Hall thruster[D].Dalian:Dalian Maritime University,2015(in Chinese).
[12] DUAN P,BIAN X Y,CAO A N,et al.Effect of segmented electrode length on the performances of an aton-type Hall thruster[J].Plasma Science and Technology 2016 5(18):525-530.
[13]胡翔,段萍,陈龙,等.霍尔推力器通道电离区壁面材料优化布置对放电特性的影响研究[C]∥第十二届中国电推进技术学术研讨会论文集,2016:447-454.HU X,DUAN P,CHEN L,et al.The influences of the wall material arrangement of ionization region on the discharge characteristics of theHall thruster channel[C]∥Proceeding of the 12th Chinese Electric Propulsion Conference,2016:447-454(in Chinese).
[14] QING S W,E P,Xia G Q,et al.Optimized electrode placement along the channel of a Hall thruster for ion focusing[J].Journal of Applied Physics,2014,115(3):736.
[15] CHOUEIRI E Y.Plasma oscillations in Hall thrusters[J].Physics of Plasmas,2001,8(4):1411-1426.
[16] PROCASSINI R J,BIRDSALL C K,MORSE E C.A fully kinetic,self-consistent particle simulation model of the collisionless plasma-sheath region[J].Physics of Fluids B Plasma Physics,1990,2(12):3191-3205.
[17] SZABO J.Fully kinetic numerical modeling of a plasma thruster[D].Boston:Massachusetts Institute of Technology,2001.
[2]张天平.国外离子和霍尔电推进技术最新进展[J].真空与低温,2006,12(4):187-193.ZHANG T P.Recent international progress in ion andHall electric propulsions[J].Vacuum and Cryogenics,2006,12(4):187-193(in Chinese).
[3]康小录,杭观荣,朱智春.霍尔电推进技术的发展与应用[J].火箭推进,2017,43(1):9-17.KANG X L,HANG G R,ZHU Z C.Development and application of Hall electric propulsion technology[J].Journal of Rocket Propulsion,2017,43(1):9-17(in Chinese).
[4]扈延林,毛威,李栋,等.面向全电推进卫星的霍尔推进技术[J].空间控制技术与应用,2017,43(1):74-78.HU Y L,MAO W,LI D,et al.The Hall propulsion technology oriented all-electric-propulsion satellites[J].Aerospace Control and Application,2017,43(1):74-78(in Chinese).
[5] AHEDOE,GALLARDO J M,MARTINEZ-SANCHEZ M.Effects of the radial plasma-wall interaction on the Hall thruster discharge[J].Physics of Plasmas,2003,10(8):3397-3409.
[6] RAITSES Y,ASHKENAZY J,APPELBAUM G,et al.Experimentalinvestigation of the effect of channel material on Hall thruster characteristics[C].International Electric Propulsion Conference,1997.
[7] XU K G,WALKER M L R.Technique tocollimate ions in a Hall-effect thruster discharge chamber[J].Journal of Propulsion&Power,2011,27(3):564-572.
[8] XU K G,DAO H,WALKER M L R.Potential contour shaping and sheath behavior with wall electrodes and near-wall magnetic fields in Hall thrusters[J].Physics of Plasmas,2012,19(10):4906.
[9] XU K,WALKER M L R.Plumecharacterization of an ion-focusing Hall thruster[J].Journal of Propulsion&Power,2015,28(5):1105-1115.
[10]李青曼,王平阳,徐宗琦.金刚石对霍尔推力器通道壁面抗溅射性能的影响[J].中国空间科学技术,2017,37(6):62-67.LI Q M,WANG P Y,XU Z Q.Effect of diamond onsputtering resistance performance of Hall thruster channel wall[J].Chinese Space Science and Technology,2017,37(6):62-67(in Chinese).
[11]曹安宁.霍尔推力器通道壁面分割放电特性研究[D].大连:大连海事大学,2015.CAO A N.Research on the discharge characteristics of channel wall segmenting in Hall thruster[D].Dalian:Dalian Maritime University,2015(in Chinese).
[12] DUAN P,BIAN X Y,CAO A N,et al.Effect of segmented electrode length on the performances of an aton-type Hall thruster[J].Plasma Science and Technology 2016 5(18):525-530.
[13]胡翔,段萍,陈龙,等.霍尔推力器通道电离区壁面材料优化布置对放电特性的影响研究[C]∥第十二届中国电推进技术学术研讨会论文集,2016:447-454.HU X,DUAN P,CHEN L,et al.The influences of the wall material arrangement of ionization region on the discharge characteristics of theHall thruster channel[C]∥Proceeding of the 12th Chinese Electric Propulsion Conference,2016:447-454(in Chinese).
[14] QING S W,E P,Xia G Q,et al.Optimized electrode placement along the channel of a Hall thruster for ion focusing[J].Journal of Applied Physics,2014,115(3):736.
[15] CHOUEIRI E Y.Plasma oscillations in Hall thrusters[J].Physics of Plasmas,2001,8(4):1411-1426.
[16] PROCASSINI R J,BIRDSALL C K,MORSE E C.A fully kinetic,self-consistent particle simulation model of the collisionless plasma-sheath region[J].Physics of Fluids B Plasma Physics,1990,2(12):3191-3205.
[17] SZABO J.Fully kinetic numerical modeling of a plasma thruster[D].Boston:Massachusetts Institute of Technology,2001.
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