外加磁场对脉冲等离子体推力器性能的影响
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摘要
为了研究外加磁场对PPT性能的影响,建立了PPT带外加磁场的机电模型,并用三种不同放电能量水平的PPT验证了该模型的可靠性。利用该模型研究了外加磁场强度、模式、位置以及长度对PPT性能的影响。结果表明,对于尾部馈送型PPT,当外加磁场增加时,PPT性能先增加后减小,存在最优的外加磁场强度。对于LES-6 PPT和LES-8/9 PPT,外加磁场从极板的最左端开始施加效果最好;当外加磁场强度分别为0.25T,0.50T,0.75T,1.00T时,这两种PPT对应的最适合施加磁场长度分别是1.3mm,1.8mm,2.1mm,2.3mm和1.6mm,2.8mm,3.4mm,3.7mm。对于TMU PPT,外加磁场从极板的最右端开始施加效果最好,但是施加磁场长度应该根据具体实验结果并结合仿真计算来决定。
In order to study the effects of applied magnetic field on the performance of PPT,an electromechanical model of PPT with an applied magnetic field was established,and the reliability of the model was verified by using three kinds of PPT with different discharge energy levels. Then,the effects of the intensity,mode,position and length of the applied magnetic field on the performance of PPT were studied by using the model. The results show that for the breech-fed PPT,the performance of PPT increases first and then decreases when the applied magnetic field increases,and the optimal applied magnetic field intensity exists. For LES-6 PPT and LES-8/9 PPT,the applied magnetic field was best applied from the far left end of the plate. When the applied magnetic field intensity was 0.25 T,0.50 T,0.75 T and 1.00 T,the optimum applied magnetic field lengths of these two PPT were 1.3 mm,1.8 mm,2.1 mm,2.3 mm and 1.6 mm,2.8 mm,3.4 mm,3.7 mm respectively. For TMU PPT,the applied magnetic field was best applied from the far right end of the plate,but the length of the applied magnetic field should be determined according to the experimental results and the simulation results.
In order to study the effects of applied magnetic field on the performance of PPT,an electromechanical model of PPT with an applied magnetic field was established,and the reliability of the model was verified by using three kinds of PPT with different discharge energy levels. Then,the effects of the intensity,mode,position and length of the applied magnetic field on the performance of PPT were studied by using the model. The results show that for the breech-fed PPT,the performance of PPT increases first and then decreases when the applied magnetic field increases,and the optimal applied magnetic field intensity exists. For LES-6 PPT and LES-8/9 PPT,the applied magnetic field was best applied from the far left end of the plate. When the applied magnetic field intensity was 0.25 T,0.50 T,0.75 T and 1.00 T,the optimum applied magnetic field lengths of these two PPT were 1.3 mm,1.8 mm,2.1 mm,2.3 mm and 1.6 mm,2.8 mm,3.4 mm,3.7 mm respectively. For TMU PPT,the applied magnetic field was best applied from the far right end of the plate,but the length of the applied magnetic field should be determined according to the experimental results and the simulation results.
引文
[1] Rycroft M,Crosby N. Smaller Satellites:Bigger Business? Concepts,Applications and Markets for Micro/Nanosatellites in a New Information World[M]. Berlin:Springer Science&Business Media,2013.
[2]谭胜,吴建军,张宇,等.激光支持的空间微推进技术研究进展[J].推进技术,2018,39(11):2415-2428.(TAN Sheng,WU Jian-jun,ZHANG Yu,et al. Research Progress of Laser-Supported Space Micropropulsion Technology[J]. Journal of Propulsion Technology,2018,39(11):2415-2428.)
[3]尤政.空间微系统与微纳卫星[M].北京:国防工业出版社,2013.
[4] Burton R L,Turchi P J. Pulsed Plasma Thruster[J].Journal of Propulsion and Power,1998,14(5):716-735.
[5]吴汉基,蒋远大,张志远.电推进技术的应用与发展趋势[J].推进技术,2003,24(5):385-392.(WU Han-ji,JIANG Yuan-da,ZHANG Zhi-yuan. Application and Development Trend of Electric Propulsion Technology[J]. Journal of Propulsion Technology,2003,24(5):385-392.)
[6] Molina-Cabrera P,Herdrich G,Lau M,et al. Pulsed Plasma Thrusters:a Worldwide Review and Long Yearned Classification[C]. Wiesbaden,Germany:32nd International Electric Propulsion Conference,2011.
[7] Sch?nherr T,Komurasaki K,Herdrich G. Propellant Utilization Efficiency in a Pulsed Plasma Thruster[J].Journal of Propulsion and Power,2013,29(6):1478-1487.
[8] Fruchtman A. Limits on the Efficiency of Several Electric Thruster Configurations[J]. Physics of Plasmas,2003,10(5):2100-2107.
[9] Kimura I,Yanagi R,Inoue S. Preliminary Experiments on Pulsed Plasma Thrusters with Applied Magnetic Fields[R]. AIAA 78-655.
[10] Kimura I,Ogiwara K,Yanagi R,et al. Effect of Applied Magnetic Fields on a Solid-Propellant Pulsed Plasma Thruster[R]. AIAA 79-2098.
[11] Takegahara H,Ohtsuka T. Performance Improvement Study of Pulsed Teflon Plasma Thruster,PartⅠ:Effects of Applied Magnetic Field on Performance[J]. Japan Society for Aeronautical and Space Sciences,1993,41:37-44.
[12] Kozawa S. Trends and Problems in Research of Permanent Magnets for Motors-Addressing Scarcity Problems of Rare Earth Elements[J]. Science&Technology Trends,2011,38:40-54.
[13] Mori S,Shindo T,Tajiri K,et al. Effects of Electric Charge in Capacitors on Pulsed Plasma Thruster Performance with External Magnetic Field[C]. Washington:33rd International Electric Propulsion Conference,2013.
[14]张代贤.激光支持的脉冲等离子体推力器理论、实验与仿真研究[D].长沙:国防科技大学,2014.
[15]张华,吴建军,张代贤,等.用于脉冲等离子体推力器烧蚀过程仿真的新型机电模型[J].物理学报,2013,62(21).
[16]侯大立,赵万生,康小明.脉冲等离子体推力器的性能分析[J].推进技术,2008,29(3):377-380.(HOU Da-li,ZHAO Wan-sheng,KANG Xiao-ming.Performance Analysis of Pulsed Plasma Thruster[J].Journal of Propulsion Technology,2008,29(3):377-380.)
[17] Turchi P J,Mikellides P G. Modeling of Ablation-Fed Pulsed Plasma Thrusters[R]. AIAA 95-2915.
[18]尹乐,周进,缪万波,等.脉冲等离子体推力器放电波形设计评估仿真研究[J].推进技术,2010,31(4):490-495.(YIN Le,ZHOU Jin,MIAO Wan-bo,et al. Design and Simulation of the Discharge Current Wave for Pulsed Plasma Thruster[J]. Journal of Propulsion Technology,2010,31(4):490-495.)
[19]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 Le,ZHOU Jin,MIAO Wan-bo,et al.Simulation of Propellant Ablation and Conduction of Pulsed Plasma Thruster[J]. Journal of Propulsion Technology,2010,31(5):623-628.)
[20]杨磊,刘向阳,陈成权,等.脉冲等离子体推力器宏观特性数值研究[J].推进技术,2011,32(6):776-780.(YANG Lei, LIU Xiang-yang, CHEN Cheng-quan,et al. Numerical Analysis on Macro-Characteristics of Pulsed Plasma Thruster[J]. Journal of Propulsion Technology,2011,32(6):776-780.)
[21]张锐.脉冲等离子体推力器工作过程仿真研究[D].长沙:国防科技大学,2008.
[22] Vondra R,Thomassen K,Solbes A. Analysis of Solid Teflon Pulsed Plasma Thruster[R]. AIAA 70-179.
[23] Shaw P V,Lappas V J. Mathematical Modeling of High Efficiency Pulsed Plasma Thrusters for Microsatellites[C]. Valencia:57th International Astronautical Congress,2006.
[2]谭胜,吴建军,张宇,等.激光支持的空间微推进技术研究进展[J].推进技术,2018,39(11):2415-2428.(TAN Sheng,WU Jian-jun,ZHANG Yu,et al. Research Progress of Laser-Supported Space Micropropulsion Technology[J]. Journal of Propulsion Technology,2018,39(11):2415-2428.)
[3]尤政.空间微系统与微纳卫星[M].北京:国防工业出版社,2013.
[4] Burton R L,Turchi P J. Pulsed Plasma Thruster[J].Journal of Propulsion and Power,1998,14(5):716-735.
[5]吴汉基,蒋远大,张志远.电推进技术的应用与发展趋势[J].推进技术,2003,24(5):385-392.(WU Han-ji,JIANG Yuan-da,ZHANG Zhi-yuan. Application and Development Trend of Electric Propulsion Technology[J]. Journal of Propulsion Technology,2003,24(5):385-392.)
[6] Molina-Cabrera P,Herdrich G,Lau M,et al. Pulsed Plasma Thrusters:a Worldwide Review and Long Yearned Classification[C]. Wiesbaden,Germany:32nd International Electric Propulsion Conference,2011.
[7] Sch?nherr T,Komurasaki K,Herdrich G. Propellant Utilization Efficiency in a Pulsed Plasma Thruster[J].Journal of Propulsion and Power,2013,29(6):1478-1487.
[8] Fruchtman A. Limits on the Efficiency of Several Electric Thruster Configurations[J]. Physics of Plasmas,2003,10(5):2100-2107.
[9] Kimura I,Yanagi R,Inoue S. Preliminary Experiments on Pulsed Plasma Thrusters with Applied Magnetic Fields[R]. AIAA 78-655.
[10] Kimura I,Ogiwara K,Yanagi R,et al. Effect of Applied Magnetic Fields on a Solid-Propellant Pulsed Plasma Thruster[R]. AIAA 79-2098.
[11] Takegahara H,Ohtsuka T. Performance Improvement Study of Pulsed Teflon Plasma Thruster,PartⅠ:Effects of Applied Magnetic Field on Performance[J]. Japan Society for Aeronautical and Space Sciences,1993,41:37-44.
[12] Kozawa S. Trends and Problems in Research of Permanent Magnets for Motors-Addressing Scarcity Problems of Rare Earth Elements[J]. Science&Technology Trends,2011,38:40-54.
[13] Mori S,Shindo T,Tajiri K,et al. Effects of Electric Charge in Capacitors on Pulsed Plasma Thruster Performance with External Magnetic Field[C]. Washington:33rd International Electric Propulsion Conference,2013.
[14]张代贤.激光支持的脉冲等离子体推力器理论、实验与仿真研究[D].长沙:国防科技大学,2014.
[15]张华,吴建军,张代贤,等.用于脉冲等离子体推力器烧蚀过程仿真的新型机电模型[J].物理学报,2013,62(21).
[16]侯大立,赵万生,康小明.脉冲等离子体推力器的性能分析[J].推进技术,2008,29(3):377-380.(HOU Da-li,ZHAO Wan-sheng,KANG Xiao-ming.Performance Analysis of Pulsed Plasma Thruster[J].Journal of Propulsion Technology,2008,29(3):377-380.)
[17] Turchi P J,Mikellides P G. Modeling of Ablation-Fed Pulsed Plasma Thrusters[R]. AIAA 95-2915.
[18]尹乐,周进,缪万波,等.脉冲等离子体推力器放电波形设计评估仿真研究[J].推进技术,2010,31(4):490-495.(YIN Le,ZHOU Jin,MIAO Wan-bo,et al. Design and Simulation of the Discharge Current Wave for Pulsed Plasma Thruster[J]. Journal of Propulsion Technology,2010,31(4):490-495.)
[19]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 Le,ZHOU Jin,MIAO Wan-bo,et al.Simulation of Propellant Ablation and Conduction of Pulsed Plasma Thruster[J]. Journal of Propulsion Technology,2010,31(5):623-628.)
[20]杨磊,刘向阳,陈成权,等.脉冲等离子体推力器宏观特性数值研究[J].推进技术,2011,32(6):776-780.(YANG Lei, LIU Xiang-yang, CHEN Cheng-quan,et al. Numerical Analysis on Macro-Characteristics of Pulsed Plasma Thruster[J]. Journal of Propulsion Technology,2011,32(6):776-780.)
[21]张锐.脉冲等离子体推力器工作过程仿真研究[D].长沙:国防科技大学,2008.
[22] Vondra R,Thomassen K,Solbes A. Analysis of Solid Teflon Pulsed Plasma Thruster[R]. AIAA 70-179.
[23] Shaw P V,Lappas V J. Mathematical Modeling of High Efficiency Pulsed Plasma Thrusters for Microsatellites[C]. Valencia:57th International Astronautical Congress,2006.
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