一种新型Z-Pinch PPT的设计和试验
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摘要
提出一种基于Z-Pinch原理但无需火花塞而自点火新型微脉冲等离子体推力器(Z-Pinch SIPPT)。为了降低推力器的点火电压以及去掉尺寸减小和轻量化的限制,采用点火和放电一体化的改性聚四氟乙烯为推进剂,两个电极分别为钉状阳极和中心有孔的阴极。相比于传统Z-Pinch PPT和平行板脉冲等离子体推力器,该推力器的优点是没有活动部件、火花塞以及为火花塞供电的电源,结构更加简单紧凑。目前研制的该型推力器本体尺寸包络仅有21mm左右,质量为15g。在保持较大推功比优势基础上,点火放电的电压峰值仅为同样自点火的同轴PPT的24%,气体PPT的2.4%。真空舱内多次点火实现累计脉冲1万多次的试验结果表明,该推力器点火电压为480V,推功比为17.83μN/W,平均推力为85.6μN。
A new type of pulsed plasma thrusters based on the Z-Pinch principle without igniters was developed.In order to reduce the discharge voltage and size,the discharge chamber consists of a solid inner anode and a hollow cathode with an orifice.The space between the electrodes is occupied by a hollow cylindrical bar of modified polytetrafluoroethylene(PTFE)propellant which can be self-ignited.Compared with conventional Z-Pinch PPT and pulsed plasma thrusters in the literature,the advantages of this new PPT lie in no moving parts,igniter and igniter power supply.The envelope size of this PPT is about 21 mm and the mass is 15 g.Based on the advantage of highthrust-to-power ratio,the discharge voltage peak of the new PPT is 24% of the coaxial PPT,and2.4% of the gas-fed PPT.Experiment result based on over ten thousand shots shows that this PPT works well,and the ignition voltage is 480 V,the thrust-to-power ratio is 17.83 N/W and thrust is 85.6 N.
A new type of pulsed plasma thrusters based on the Z-Pinch principle without igniters was developed.In order to reduce the discharge voltage and size,the discharge chamber consists of a solid inner anode and a hollow cathode with an orifice.The space between the electrodes is occupied by a hollow cylindrical bar of modified polytetrafluoroethylene(PTFE)propellant which can be self-ignited.Compared with conventional Z-Pinch PPT and pulsed plasma thrusters in the literature,the advantages of this new PPT lie in no moving parts,igniter and igniter power supply.The envelope size of this PPT is about 21 mm and the mass is 15 g.Based on the advantage of highthrust-to-power ratio,the discharge voltage peak of the new PPT is 24% of the coaxial PPT,and2.4% of the gas-fed PPT.Experiment result based on over ten thousand shots shows that this PPT works well,and the ignition voltage is 480 V,the thrust-to-power ratio is 17.83 N/W and thrust is 85.6 N.
引文
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[8]张华,吴建军,何振.等脉冲等离子体推力器等离子体羽流的光谱研究[J].光谱学与光谱分析,2016,36(6):1867-1871.ZHANG H,WU J J,HE Z,et al.Study on plasma characteristics in a pulsed plasma thruster by optical emission spectroscopy[J].Spectroscopy and Spectral Analysis,2016,36(6):1867-1871(in Chinese).
[9]王尚民,张家良,张天平,等.μ-PPT等离子体电子密度氢光谱诊断技术[J].中国空间科学技术,2016,36(1):94-102.WANG S M,ZHANG G L,ZHANG T P,et al.A diagnostic scheme for electron density inμ-PPT plasma using H Stark broadening[J].Chinese Space Science and Technology,2016,36(1):94-102(in Chinese).
[10]王尚民,田立成,张家良,等.微脉冲等离子体推力器放电过程和性能初探[J].中国空间科学技术,2017,37(5):24-32.WANG S M, TIAN L C, ZHANG J L,et al.Elementary study on the discharge process and performance of micro-pulsed plasma thruster[J].Chinese Space Science and Technology,2017,37(5):24-32(in Chinese).
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[12] ANTIPOV A A,BOGATYY A B.Simulation of the motion of charged particles in an ablative pulsed plasma thruster at the initial stage of the discharge[C].6th Russian-German Conference on Electric Propulsion and Their Application,2017.
[13]谭北华.一种同轴脉冲等离子体微推力器的研制与测试[D].北京:中国科学院研究生院,2003.TAN B H.Design and test of a coaxial micro-pulsed plasma thruster[D].Beijing:Graduate University of Chinese Academy of Science,2003(in Chinese).
[14] HIROSHI H,NAO A,KOUTA M,et al.Discharge Characteristics of a gas-fed short-pulse plasma thruster[C].Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric Propulsion Conference and 6th Nano-satellite Symposium,Kobe-Hyogo,2015:1-6.
[15] JAHN R G,VON JASKOWSKY W,BURTON,R L.Ejection of a pinched plasma from an axial orifice[J].AIAA Journal,1965,3(10):1862–1866.
[16] THOMAS E M,KURT A P,EDGAR Y C,et al.Ablative Z-pinch pulsed plasma thruster[J].Journal of Propulsion and Power,2005,21(3):392-400.
[17]陈光华,但加坤,刘俊.用于Z箍缩实验的多幅激光差分干涉与阴影成像诊断系统[J].中国激光,2015,42(12):1-6.CHEN G H,DAN J K,LIU J.Multiframe laser differential interferometer and shadowgraph system for Z-pinch experiments[J].Chinese Journal of Lasers,2015,42(12):1-6(in Chinese).
[18]阳庆国,黄显宾,刘冬兵,等.聚龙一号装置上首次铝套筒Z箍缩X射线背光照相实验[J].强激光与离子束.2016,28(4):1-3.YANG Q G,HUANG X B,LIU D B,et al.The first XraybacklightingofZ-pinchedaluminiumliner experiment on PTS facility[J].High Power Laser and Particle Beams.2016,28(4):1-3(in Chinese).
[19]周林,李正宏,梁川,等.基于LTD技术900kA的Z箍缩驱动器设计[J].太赫兹科学与电子信息学报.2017,15(3):513-517.ZHOU L,LI Z H,LIANG C,et al.Design of a 900kA LTD accelerator for wire-array Z-pinch experiments[J].Journal of Terahertz Science and Electronic Information Technology.2017,15(3):513-517(in Chinese).
[20]莫永刚,陈志林,宋鸿鹄,等.Z箍缩驱动聚变-裂变混合堆氚燃料循环系统氚盘存量与氚自持初步分析[J].强激光与离子束.2017,29(11):1-5.MO Y G,CHEN Z L,SONG H H,et al.Tritium inventory and tritium self-sufficiency of tritium fuel cycle system in Z-pinch driven fusion-fission hybrid reactor(ZFFR)[J].High Power Laser and Particle Beams.2017,29(11):1-5(in Chinese).
[21] KATERYNA A,KAZUHIRO T,MENGU C.Vacuum arc thruster development and testing for micro-and nano satellites[C].Joint Conference of 30th International Symposium on Space Technologyand Science 34th International Electric Propulsion Conference and 6th Nanosatellite Symposium,Hyogo-Kobe:2015.
[2]侯大立,赵万生,康小明.脉冲等离子体推力器火花塞的性能实验[J].推进技术,2007,28(6):679-682.HOU D L,ZHAO W S,KANG X M.Experiment on spark plug of pulsed plasma thruster[J].Journal of Propulsion Technology,2007,28(6):679-682(in Chinese).
[3]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.YANG L.Theoretical andexperimental study of pulsed plasma thruster operation process[D].Changsha:National University of Defense Technology,2007(in Chinese).
[4]李自然.脉冲等离子体推力器设计与性能的理论与实验研究[D].长沙:国防科学技术大学,2008.LI Z R.Theoretical and experimental study of pulsed plasma thruster design and performance[D].Changsha:National University of Defense Technology,2007(in Chinese).
[5]尹乐,周进,缪万波,等.脉冲等离子体推力器推进剂烧蚀传热计算[J].推进技术,2010,31(5):623-628.YIN L,ZHOU J,MIAO W B,et al.Simulation of propellant ablation and conduction of pulsed plasma thruster[J].Journal of Propulsion Technology,2010,1(5):623-628(in Chinese).
[6]谢泽华.固体烧蚀型脉冲等离子体推力器工作特性研究[D].长沙:国防科学技术大学,2013.XIE Z H.Study on operating characteristics of ablationfed pulsed plasma thrusters[D].Changsha:National University of Defense Technology,2007(in Chinese).
[7]朱迎超.脉冲等离子体推力器推力测试及光谱特性实验研究[D].北京:北京理工大学,2015.ZHU Y C.Development of thrust measure and spectral characteristics of pulsed plasma thruster[D],Beijing:Beijing Institute of Technology,2015(in Chinese).
[8]张华,吴建军,何振.等脉冲等离子体推力器等离子体羽流的光谱研究[J].光谱学与光谱分析,2016,36(6):1867-1871.ZHANG H,WU J J,HE Z,et al.Study on plasma characteristics in a pulsed plasma thruster by optical emission spectroscopy[J].Spectroscopy and Spectral Analysis,2016,36(6):1867-1871(in Chinese).
[9]王尚民,张家良,张天平,等.μ-PPT等离子体电子密度氢光谱诊断技术[J].中国空间科学技术,2016,36(1):94-102.WANG S M,ZHANG G L,ZHANG T P,et al.A diagnostic scheme for electron density inμ-PPT plasma using H Stark broadening[J].Chinese Space Science and Technology,2016,36(1):94-102(in Chinese).
[10]王尚民,田立成,张家良,等.微脉冲等离子体推力器放电过程和性能初探[J].中国空间科学技术,2017,37(5):24-32.WANG S M, TIAN L C, ZHANG J L,et al.Elementary study on the discharge process and performance of micro-pulsed plasma thruster[J].Chinese Space Science and Technology,2017,37(5):24-32(in Chinese).
[11] SABRINA J P,DAVID K,CARSTEN A S.Pulsed plasma thrusterperformanceforminiaturizedelectrode configurations and low energy operation[J].Acta Astronautica,2011,68:1996-2004.
[12] ANTIPOV A A,BOGATYY A B.Simulation of the motion of charged particles in an ablative pulsed plasma thruster at the initial stage of the discharge[C].6th Russian-German Conference on Electric Propulsion and Their Application,2017.
[13]谭北华.一种同轴脉冲等离子体微推力器的研制与测试[D].北京:中国科学院研究生院,2003.TAN B H.Design and test of a coaxial micro-pulsed plasma thruster[D].Beijing:Graduate University of Chinese Academy of Science,2003(in Chinese).
[14] HIROSHI H,NAO A,KOUTA M,et al.Discharge Characteristics of a gas-fed short-pulse plasma thruster[C].Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric Propulsion Conference and 6th Nano-satellite Symposium,Kobe-Hyogo,2015:1-6.
[15] JAHN R G,VON JASKOWSKY W,BURTON,R L.Ejection of a pinched plasma from an axial orifice[J].AIAA Journal,1965,3(10):1862–1866.
[16] THOMAS E M,KURT A P,EDGAR Y C,et al.Ablative Z-pinch pulsed plasma thruster[J].Journal of Propulsion and Power,2005,21(3):392-400.
[17]陈光华,但加坤,刘俊.用于Z箍缩实验的多幅激光差分干涉与阴影成像诊断系统[J].中国激光,2015,42(12):1-6.CHEN G H,DAN J K,LIU J.Multiframe laser differential interferometer and shadowgraph system for Z-pinch experiments[J].Chinese Journal of Lasers,2015,42(12):1-6(in Chinese).
[18]阳庆国,黄显宾,刘冬兵,等.聚龙一号装置上首次铝套筒Z箍缩X射线背光照相实验[J].强激光与离子束.2016,28(4):1-3.YANG Q G,HUANG X B,LIU D B,et al.The first XraybacklightingofZ-pinchedaluminiumliner experiment on PTS facility[J].High Power Laser and Particle Beams.2016,28(4):1-3(in Chinese).
[19]周林,李正宏,梁川,等.基于LTD技术900kA的Z箍缩驱动器设计[J].太赫兹科学与电子信息学报.2017,15(3):513-517.ZHOU L,LI Z H,LIANG C,et al.Design of a 900kA LTD accelerator for wire-array Z-pinch experiments[J].Journal of Terahertz Science and Electronic Information Technology.2017,15(3):513-517(in Chinese).
[20]莫永刚,陈志林,宋鸿鹄,等.Z箍缩驱动聚变-裂变混合堆氚燃料循环系统氚盘存量与氚自持初步分析[J].强激光与离子束.2017,29(11):1-5.MO Y G,CHEN Z L,SONG H H,et al.Tritium inventory and tritium self-sufficiency of tritium fuel cycle system in Z-pinch driven fusion-fission hybrid reactor(ZFFR)[J].High Power Laser and Particle Beams.2017,29(11):1-5(in Chinese).
[21] KATERYNA A,KAZUHIRO T,MENGU C.Vacuum arc thruster development and testing for micro-and nano satellites[C].Joint Conference of 30th International Symposium on Space Technologyand Science 34th International Electric Propulsion Conference and 6th Nanosatellite Symposium,Hyogo-Kobe:2015.