Pulsed plasma thruster (PPT) is a promising electric propulsion device with simple structure and high specific impulse,and it can be used for attitude control and position keeping of micro-satellite. The electrical parameters (resistance and inductance) of the discharge circuit of PPT can provide a reference for the optimization of PPT performance. We employed the Segmentation Formula Fitting Method to calculate the electrical parameters.The primary discharge is divided into two parts for calculation. The experimental data can be made full use of and the range of electrical parameters in the process of discharge can be calculated by the method compared with the eigenvalue method. The results show that the resistance increases and the inductance decreases during the discharge, and the electrical parameters are related to the discharge voltage. The resistance increases with the decrease of the initial voltage, but the inductance hardly changes. For plasma energy distribution, the changing plasma parameters mainly affect the magnetic energy in the early stage of discharge and the deposition energy in the final stage of discharge.
KEY WORDS :pulsed plasma thruster;plasma electrical parameters;eigenvalue method;segmentation formula fitting method;energy distribution;
在PPT电参数研究领域,RL Burton等人采用特征值法计算回路电阻、电感[8]。该方法仅利用了两个相邻峰值点的数据,因而只能粗略地估算出电阻、电感;Joshua L. Rovey对特征值法进行了改进,其认为放电曲线的振荡周期主要由电感决定,幅值主要由电阻决定[9]。通过先确定电感,然后选择不同的电阻值以使得仿真电流与实际电流的残差平方和最小;丁卫东利用特征值法求得的等离子体电阻、电感计算电热式PPT放电通道内的纯电阻焦耳热能,并分析其放电特性[10]。
图10
不同初始电压下PPT沉积能量对比
Fig.10
Deposition energy of different initial voltage of PPT
图11
不同初始电压下PPT磁能对比
Fig.11
Magnetic energy of different initial voltage of PPT
3)随着放电的进行,等离子体电阻增大,等离子体电感减小,初始电压主要影响放电末期的电阻变化。
4)等离子体能量分布上,变化的等离子体电参数主要影响放电前期的磁能和放电后期的沉积能量。
参考文献
[1]
GUMAN WJ, NATHANSON DM.Pulsed plasma microthruster propulsion system for synchronous orbit satellite[J]. , 1970, 7(4): 409-415.
[2]
AN SM, WU HJ, FENG XZ, et al.Space flight test of electric thruster system MDT-2A[J]. , 2015, 21(6): 593-594.
[3]
姜齐荣,王亮,谢小荣. 电力电子化电力系统的振荡问题及其抑制措施研究[J]. ,2017,43(4):1057-1066.JIANGQirong, WANGLiang, XIEXiaorong.Study on oscillations of power-electronized power system and their mitigation schemes[J]. , 2017, 43(4): 1057-1066.
[4]
张琛,蔡旭,李征. 电压源型并网变流器的机-网电气振荡机理及稳定判据研究[J]. ,2017,37(11):3174-3183.ZHANGChen, CAIXu, LIZheng, et al.Stability criterion and mechanisms analysis of electrical oscillations in the grid-tied VSC system[J]. , 2017, 37(11): 3174-3183.
[5]
李金宇,祝令瑜,熊易,等. 滤波电容器振动与噪声多倍频现象及其产生机理模型[J]. ,2018,44(6):2081-2088.LIJinyu, ZHULingyu, XIONGYi, et al.Mechanism model of multi-times-frequency spectrum of filter capacitor vibration and audible noise[J]. , 2018, 44(6): 2081-2088.
[6]
BANERJEEK, MEHROTRAA.Analysis of on-chip inductance effects for distributed RLC interconnects[J]. , 2002, 21(8): 904-915.
[7]
谢慧瑷. [M]. 北京:北京大学出版社,1990.XIEHui’ai.[M]. Beijing, China: Peking University Press, 1990.
[9]
杨磊,刘向阳,王司宇,等. 基于不同烧蚀模型的脉冲等离子体推力器壁面-等离子体交互作用的机理[J]. ,2013,39(9):2301-2308.YANGLei, LIUXiangyang, WANGSiyu, et al.Different ablation models for the wall-plasma interaction process in pulsed plasma thruster[J]. , 2013, 39(9): 2301-2308.
[10]
CHENGL, DING WD, et al.Preliminary study on discharge characteristics in a capillary discharge based pulsed plasma thruster for small satellites[C]∥The International Electric Propulsion Conference. Atlanta, , 2017.
[11]
VONDRAR, THOMASSENK, SOLBES A.A pulsed electric thruster for satellite control[J]. , 1971, 59(2): 271-277.
[12]
吴汉基,蒋远大,张志远. 电推进技术的应用与发展趋势[J]. ,2003,24(5):385-392.WUHanji, JIANGYuanda, ZHANGZhiyuan.Application and development trend of electricpropulsion technology[J]. , 2003, 24(5): 385-392.
[13]
王小艳. 非线性RLC电路特性的数字仿真研究[J]. ,2001,37(6):52-54.WANGXiaoyan.Numerical simulation of nonlinear RLC electric circuit characteristics[J]. , 2001, 37(6): 52-54.
[14]
MIKELLIDES PG.Theoretical modeling and optimization of ablation-fed pulsed plasma thruster[D]. Columbus, , 1999.
[15]
WONG CS, CHOIP, SERGUEIT.Preliminary results on a pulsed capillary discharge[C]∥American Institute of Physics. [S.l.]: , 1997: 417-421.
[16]
侯大力,康小明,赵万生,等. 脉冲等离子体推力器等效电路模型分析[J]. ,2008,31(5):480-483.HOUDali, KANGXiaoming, ZHAOWansheng, et al.Analysis of equivalent circuit model for pulsed plasma thruster[J]. , 2008, 31(5): 480-483.
[17]
姜慧,邵涛,车学科,等. 纳秒脉冲表面放电等离子体影响因素的实验研究[J]. ,2012,38(7):1704-1710.JIANGHui, SHAOTao, CHEXueke, et al.Experimental study on the factors influencing nanosecond-pulsed surface discharge plasma[J]. , 2012, 38(7): 1704-1710.
[19]
JIANGH, SHAOS, ZHANGC, et al.Distribution characteristics of nanosecond-pulsed surface dielectric barrier discharge at different electrode gaps[J]. , 2017, 32(2): 33-42.
[20]
KOIZUMIH, NOJIR, KOMURASAKIK, et al.3(2007): 033506.
[21]
HUANG TK, WU ZW, LIU XY, et al.Modeling of gas ionization and plasma flow in ablative pulsed plasma thrusters[J]. , 2016, 129: 309-315.
[22]
陈坚,向金秋,郭恒,等. 基于一维电子平衡流体模型的平行板离子引出数值模拟[J]. ,2017,43(6):1830-1836.CHENJian, XIANGJinqiu, GUOHeng, et al.One-dimension modeling on parallel-plate ion extraction process based on electron-equilibrium fluid model[J]. , 2017, 43(6): 1830-1836.
[23]
荣命哲,仲林林,王小华,等. 平衡态与非平衡态电弧等离子体微观特性计算研究综述[J]. ,2016,31(19):54-65.RONGMingzhe, ZHONGLinlin, WANGXiaohua, et al.Review of microscopic property calculation of equilibrium and non-equilibrium arc plasma[J]. , 2016, 31(19): 54-65.
[24]
韩桂全,刘洋,刘庆,等. 铜蒸气对CO2电弧等离子体物性参数的影响[J]. ,2018,44(5):1635-1640.HANGuiquan, LIUYang, LIUQing, et al.Effect of Cu vapour on the physical property parameters of CO2 arc plasma[J]. , 2018, 44(5): 1635-1640.
[25]
SPITZERL.Physics of fully ionized gasses[M]. , 1956.
[26]
CHENGX, LIUX, WUZ, et al.Two-stream model of the pulsed plasma thruster and simulation research[C]∥The International Electric Propulsion Conference. Atlanta, , 2017.