脉冲等离子体推力器放电电离二维PIC建模与仿真
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摘要
针对脉冲等离子体推力器(PPT)的放电过程,利用粒子网格-蒙特卡洛(PIC-MCC)方法建立仿真计算模型.以LES-6 PPT为例,加入电离碰撞进行电离仿真.通过粒子运动碰撞与电磁场耦合仿真计算得到电流与电路总电阻的变化规律,揭示了PPT放电过程中等离子体密度分布情况.通过对比不加入粒子预分布与加入粒子预分布的两种条件下的计算结果,得到了加入粒子预分布使带电粒子密度计算结果更接近实验结果的结论.根据PPT的工作过程,在放电之前推力器内存在等离子体,所以在仿真研究中应进行粒子的预分布.文中的研究方法对PPT的粒子方法模拟具有一定的参考意义.
A particle-in-cell method with Monte Carlo collision( PIC-MCC) model is established for the discharge process in pulsed plasma thruster( PPT). The ionization process in LES-6 PPT is simulated,considering the ionization collisions. According to the coupling computation of particle movement,collisions and electromagnetic field,the curves of current and resistance are acquired,and the distributions of plasma during the discharge of PPT are presented. Two initial conditions with and without particles predistribution are applied respectively to the numerical computation,implying that the results in the case with the pre-distribution are closer to the experimental results. The results in the other case tend to be in accordance with the results in the ignition process. The methods and model explored in this work provide a certain reference for PIC simulations in PPT.
A particle-in-cell method with Monte Carlo collision( PIC-MCC) model is established for the discharge process in pulsed plasma thruster( PPT). The ionization process in LES-6 PPT is simulated,considering the ionization collisions. According to the coupling computation of particle movement,collisions and electromagnetic field,the curves of current and resistance are acquired,and the distributions of plasma during the discharge of PPT are presented. Two initial conditions with and without particles predistribution are applied respectively to the numerical computation,implying that the results in the case with the pre-distribution are closer to the experimental results. The results in the other case tend to be in accordance with the results in the ignition process. The methods and model explored in this work provide a certain reference for PIC simulations in PPT.
引文
[1]毛根旺,唐金兰.航天器推进系统及其应用[M].西安:西北工业大学出版社,2009.
[2]SPANJERSG G,LOTSPEICH J S,MCFALL K A,et al.Propellant losses because of particulate emission in a pulsed plasma thruster[J].Journal of Propulsion&Power,1998,14(4):554-559.
[3]RYOSUKE N,KIMIYA K,YOSHIHIRO A.Study on plasma acceleration in an ablative pulsed plasma thruster[C]//Proceedings of the 43rdAIAA/ASME/SAE/ASEE,Joint Propulsion Conference and Exhibit.Washington D.C.:AIAA 2007-5226,2007.
[4]NEUDORFER J,STINDLB T,SCNNEIDER R.Threedimensional particle-in-cell simulation of a pulsed plasma thruster:modeling and challenges[C]//The 32ndInternational Electric Propulsion Conference.Wiesbaden Germany:IEPC-2011-116,2011.
[5]HUANGT,WU Z,LIU X,et al.Modeling of gas ionization and plasma flow in ablative pulsed plasma thrusters[J].Acta Astronautica,2016,129:309-315.
[6]ANTIPOVA A,BOGATYY A B.Simulation of the motion of charged particles in an ablative pulsed plasma thruster at the initial stage of the discharge[J].Procedia Engineering,2017,185:61-68.
[7]邓健.脉冲等离子体推进器脉冲电源及推进剂烧蚀特性的实验研究和数值分析[D].南京理工大学,2013.
[8]YANG L,ZENG G,TANG H,et al.Numerical studies of wall-plasma interactions and ionization phenomena in an ablative pulsed plasma thruster[J].Physics of Plasmas,2016,23(7):716-15.
[9]SCHNHERRT,NEES F,ARAKAWA Y,et al.Characteristics of plasma properties in an ablative pulsed plasma thruster[J].Physics of Plasmas,2013,20(3):1310-563.
[10]BOYDI D,KEIDAR M,MCKEON W.Modeling of a pulsed plasma thruster from plasma generation to plume far field[J].Journal of Spacecraft&Rockets,1971,37(3):399-407.
[11]GATSONISN A,YIN X.Hybrid(particle-fluid)modeling of pulsed plasma thruster plumes[J].Journal of Propulsion&Power,2015,17(5):945-958.
[12]VAHEDI V,SURENDRA M.A Monte Carlo collision model for the particle-in-cell method:applications to argon and oxygen discharges[J].Computer Physics Communications,1995,87(1-2):179-198.
[13]BIRDSALLC K.Particle-in-cell charged-particle simulations,plus Monte Carlo collisions with neutral atoms,PIC-MCC[J].IEEE Transactions on Plasma Science1991,19(2):65-85.
[14]HAMIDIAN J P,DAHLGREN J B.Testing and evaluation of the LES-6 pulsed plasma thruster by means of a torsion pendulum system[R].NASA-CR-135940,1973.
[15]杨乐.脉冲等离子体推力器工作过程理论和实验研究[D].长沙:国防科学技术大学,2007.
[16]YANGL,LIU X Y,WANG S Y,et al.Theoretical and numerical analysis of discharge characteristics in pulsed electromagnetic accelerators[J].Advanced Materials Research,2013,765-767:805-808.
[17]SOLBESA,THOMASSEN K,VONDRA R.Analysis of solid teflon pulsed plasma thruster[J].Journal of Spacecraft&Rockets,1970,7(7):1402-1406.
[18]BOYDI D,KEIDAR M,MCKEON W.Modeling of a pulsed plasma thruster from plasma generation to plume far field[J].Journal of Spacecraft&Rockets,2000,37(3):399-407.
[19]YANGL,Li U X Y,et al.Different ablation models for the wall-plasma interaction process in pulsed plasma thruster[J].High Voltage Engineering,2013,39(9):2301-2308.
[20]KEITHI T.Exhaust velocity studies of a solid teflon pulsed plasma thruster[J].Journal of Spacecraft&Rockets,1972,9(1):61-64.
[2]SPANJERSG G,LOTSPEICH J S,MCFALL K A,et al.Propellant losses because of particulate emission in a pulsed plasma thruster[J].Journal of Propulsion&Power,1998,14(4):554-559.
[3]RYOSUKE N,KIMIYA K,YOSHIHIRO A.Study on plasma acceleration in an ablative pulsed plasma thruster[C]//Proceedings of the 43rdAIAA/ASME/SAE/ASEE,Joint Propulsion Conference and Exhibit.Washington D.C.:AIAA 2007-5226,2007.
[4]NEUDORFER J,STINDLB T,SCNNEIDER R.Threedimensional particle-in-cell simulation of a pulsed plasma thruster:modeling and challenges[C]//The 32ndInternational Electric Propulsion Conference.Wiesbaden Germany:IEPC-2011-116,2011.
[5]HUANGT,WU Z,LIU X,et al.Modeling of gas ionization and plasma flow in ablative pulsed plasma thrusters[J].Acta Astronautica,2016,129:309-315.
[6]ANTIPOVA A,BOGATYY A B.Simulation of the motion of charged particles in an ablative pulsed plasma thruster at the initial stage of the discharge[J].Procedia Engineering,2017,185:61-68.
[7]邓健.脉冲等离子体推进器脉冲电源及推进剂烧蚀特性的实验研究和数值分析[D].南京理工大学,2013.
[8]YANG L,ZENG G,TANG H,et al.Numerical studies of wall-plasma interactions and ionization phenomena in an ablative pulsed plasma thruster[J].Physics of Plasmas,2016,23(7):716-15.
[9]SCHNHERRT,NEES F,ARAKAWA Y,et al.Characteristics of plasma properties in an ablative pulsed plasma thruster[J].Physics of Plasmas,2013,20(3):1310-563.
[10]BOYDI D,KEIDAR M,MCKEON W.Modeling of a pulsed plasma thruster from plasma generation to plume far field[J].Journal of Spacecraft&Rockets,1971,37(3):399-407.
[11]GATSONISN A,YIN X.Hybrid(particle-fluid)modeling of pulsed plasma thruster plumes[J].Journal of Propulsion&Power,2015,17(5):945-958.
[12]VAHEDI V,SURENDRA M.A Monte Carlo collision model for the particle-in-cell method:applications to argon and oxygen discharges[J].Computer Physics Communications,1995,87(1-2):179-198.
[13]BIRDSALLC K.Particle-in-cell charged-particle simulations,plus Monte Carlo collisions with neutral atoms,PIC-MCC[J].IEEE Transactions on Plasma Science1991,19(2):65-85.
[14]HAMIDIAN J P,DAHLGREN J B.Testing and evaluation of the LES-6 pulsed plasma thruster by means of a torsion pendulum system[R].NASA-CR-135940,1973.
[15]杨乐.脉冲等离子体推力器工作过程理论和实验研究[D].长沙:国防科学技术大学,2007.
[16]YANGL,LIU X Y,WANG S Y,et al.Theoretical and numerical analysis of discharge characteristics in pulsed electromagnetic accelerators[J].Advanced Materials Research,2013,765-767:805-808.
[17]SOLBESA,THOMASSEN K,VONDRA R.Analysis of solid teflon pulsed plasma thruster[J].Journal of Spacecraft&Rockets,1970,7(7):1402-1406.
[18]BOYDI D,KEIDAR M,MCKEON W.Modeling of a pulsed plasma thruster from plasma generation to plume far field[J].Journal of Spacecraft&Rockets,2000,37(3):399-407.
[19]YANGL,Li U X Y,et al.Different ablation models for the wall-plasma interaction process in pulsed plasma thruster[J].High Voltage Engineering,2013,39(9):2301-2308.
[20]KEITHI T.Exhaust velocity studies of a solid teflon pulsed plasma thruster[J].Journal of Spacecraft&Rockets,1972,9(1):61-64.