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脉冲等离子体推力器推进剂烧蚀传热计算 被引量:5

Simulation of propellant ablation and conduction of pulsed plasma thruster
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摘要 运用磁流体动力学的方法,建立脉冲等离子体推力器工作过程模型,展开三维仿真研究,对推进剂的烧蚀传热过程进行分析。通过该模型计算得到的推进剂烧蚀质量和元冲量能够反映出实验结果的大体趋势,同时针对不同电容以及两种不同推力室构型的情况进行了评估。结果显示,推进剂的温度变化波形反映着放电波形的变化波形,影响着推力室等离子体的流动,良好的推进剂表面温度分布更有助于推进剂的喷射过程。 The work process of Pulsed Plasma Thruster was modeled by three-dimensional two-temperature MHD model through magnetohydrodynamic method to carry out three-dimensional simulation research.The propellant ablation and conduction were analyzed.The variety trends of the results of ablated mass and impulse bit agreed well with those of experiments.The cases of different capacitor and two kinds of chamber geometry were evaluated.The results show that the variety of propellant surface-temperature follows that of discharge current,which affects the flow of plasma in chamber.Good distribution of propellant surface-temperature is important for propellant ejection.
出处 《推进技术》 EI CAS CSCD 北大核心 2010年第5期623-628,共6页 Journal of Propulsion Technology
基金 国家自然科学基金资助项目(10772195)
关键词 磁流体动力学 三维双温MHD模型 脉冲等离子体推力器 工作过程 推进剂烧蚀传热 Magnetohydrodynamic Three-dimension two-temperature MHD model Pulsed plasma thruster Work process Propellant ablation and conduction
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  • 1杨乐.脉冲等离子体推力器工作过程理论和实验研究[D]国防科学技术大学,国防科学技术大学2007. 被引量:1
  • 2李瀚荪,吴锡龙编..电路分析基础 第4版 学习指导[M].北京:高等教育出版社,2006:297.
  • 3Keidar M,Boyd I D,Antonsen E Let al.Optimization issues for a micropulsed plasma thruster. Journal of Propulsion Technology . 2006 被引量:1
  • 4Thomas H D.Numerical simulation of pulsed plasma thrusters. . 2000 被引量:1
  • 5Mitchner M,Charles H,Kruger J.Partially ionized gases. . 1994 被引量:1
  • 6Sankaran K.Simulation of MPD flows using a flux-limited numerical method for the MHD equations. . 2001 被引量:1
  • 7Roe P L,Balsara D S.Notes on the eigensystem of mag-netohydrodynamics. Journal of Applied Mathematic . 1996 被引量:1
  • 8Turchi P J,Mikellides P G.Modeling of ablatin-fed pulsed plasma thrusters. AIAA 95-2915 . 被引量:1
  • 9Burton R L,,Turchi P J.Pulsed Plasma Thruster. Journal of Propulsion Technology . 1998 被引量:1

同被引文献60

  • 1Burton R L, Turch P J. Pulsed plasma thruster [ J]. Journal of Propulsion and Power, 1998,14 ( 5 ) :716-735. 被引量:1
  • 2Cassihry J T,Francis Thio Y C, Markusic T E,et al. Nu- merical modeling of a pulsed electromagnetic plasma thruster experiment[J]. Journal of Propulsion and Pow- er, 2006,22(3): 628-635. 被引量:1
  • 3Henrikson E M, Mikellides P G. Modeling of ablation-fed pulsed plasma thruster operation using a new approach to the ablation process[ R]. A1AA 2008-4645. 被引量:1
  • 4Mikellides P G. Theoretical modeling and optimization ofablation-fed pulsed plasma thrusters [ D ]. Columbus, USA: Ohio State University, 1999. 被引量:1
  • 5Hani Kamhawi, Turchi P J, Mikellides P G, et al. Ex- perimental and theoretical investigation of an inverse-pinch coaxial pulsed plasma thruster[ R]. A1AA 00-3261. 被引量:1
  • 6Thomas H D. Numerical simulation of pusled plasma thrusters [ D]. Knoxiville , USA : University of Tennessee ,2000. 被引量:1
  • 7Guang Lin, George Em Karniadakis. High-order modeling of micro-pulsed plasma thrusters[ R]. AIAA 2002-2872. 被引量:1
  • 8Micci Michael M, Ketsdever Andrew D. Micropropulsion for small spacecraft [ M I. Reston: American Institute of Aeronautics and Astronautics, 2000:357-358. 被引量:1
  • 9Burton Rodney L, Wilson Michael J, Bushman Stewart S. Energy balance and efficiency of the pulsed plasma thruster[ R]. AIAA 1998-3808. 被引量:1
  • 10Kovitya P. Thermodynamic and transport properties of ab- lated vapors of PTFE, alumina, perspex, and PVC in the temperature range 5000-30000K [ J]. 1EEE Transaction on Plasma Science, 1984, PS-12 ( 1 ) :38-42. 被引量:1

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