脉冲等离子体推力器烧蚀建模与仿真

推进技术 ›› 2011, Vol. 32 ›› Issue (6): 788-793.

脉冲等离子体推力器烧蚀建模与仿真

肖利杰,刘向阳,杨磊,武志文,王宁飞

北京理工大学宇航学院,北京100081;北京新风机械厂,北京100854;北京理工大学宇航学院,北京100081;北京理工大学宇航学院,北京100081;北京理工大学宇航学院,北京100081;北京理工大学宇航学院,北京100081

发布日期:2021-08-15
作者简介:肖利杰(1983—),男,硕士生,研究领域为脉冲等离子体电推力器。E-mail:xiaolj0@163.com
基金资助:
北京理工大学基础研究基金(20080142003)。

Ablation modeling and simulation for pulsed plasma thruster

School of Aerospace, Beijing Institute of Technology,Beijing 100081,China ;Beijing Xinfeng Machinery Factory,Beijing 100854,China;School of Aerospace, Beijing Institute of Technology,Beijing 100081,China;School of Aerospace, Beijing Institute of Technology,Beijing 100081,China;School of Aerospace, Beijing Institute of Technology,Beijing 100081,China;School of Aerospace, Beijing Institute of Technology,Beijing 100081,China

Published:2021-08-15

摘要/Abstract

摘要： 为了深入地揭示平板型脉冲等离子体推力器(PPT)工作机理,通过对PPT在放电过程中的欧姆加热能量分配分析,建立了基于能量守恒原理的改进烧蚀模型,并对磁流体动力学方程中的能量方程进行了修正。结合LES-6对PPT工作过程进行了一维磁流体动力学数值仿真,获得了PPT的速度分布、放电烧蚀质量和元冲量等参数的变化过程。仿真结果表明,改进模型能正确地反映脉冲等离子体推力器工作过程,仿真得到的出口速度、元冲量与实验值吻合较好,而放电烧蚀质量则相对误差较大；当电容容量变化时,元冲量随放电能量增大呈近似的线性增长关系,放电烧蚀质量随放电能量的增大单调增加且呈非线性关系。

关键词: 脉冲等离子体推力器;烧蚀模型;磁流体动力学;数值仿真

Abstract: To further reveal the working mechanism of Pulsed Plasma Thruster (PPT), the distribution of ohmic-heating energy was analyzed, and an improved ablation model was proposed based on conservation of energy and the energy equation of magnetohydrodynamic (MHD) equations revised. The working process of LES-6 PPT was simulated by use of the one-dimensional MHD program and the temporal variation of some parameters such as the velocity map, discharge ablation mass and impulse bit have been obtained. The results exhibit that the improved model can correctly reveal the working process of PPT and the simulated values of the exit velocity and impulse bit fit well with the experimental values while that of discharge ablation mass shows large error. It is also shown that the impulse bit almost increases linearly with the discharge energy and discharge ablation mass increases with a non-linear correlation while the capacity of the capacitors varies.

Key words: Pulsed plasma thruster; Ablation model; Magnetohydrodynamic; Numerical simulation

肖利杰,刘向阳,杨磊,武志文,王宁飞. 脉冲等离子体推力器烧蚀建模与仿真[J]. 推进技术, 2011, 32(6): 788-793.

参考文献

[2] Cassibry J T,Francis Thio Y C, Markusic T E,et al.Numerical modeling of a pulsed electromagnetic plasma thruster experiment[J] .Journal of Propulsion and Power, 6,2(3):628-635.
[3] Henrikson E M, Mikellides P G.Modeling of ablation-fed pulsed plasma thruster operation using a new approach to the ablation process[R].AIAA 2008-4645.
[4] Mikellides P G.Theoretical modeling and optimization of ablation-fed pulsed plasma thrusters[D]. Columbus, USA:Ohio State University, 1999.
[5] Hani Kamhawi, Turchi P J, Mikellides P G, et al.Experimental and theoretical investigation of an inverse-pinch coaxial pulsed plasma thruster[R].AIAA 00-3261.
[6] Thomas H D.Numerical simulation of pusled plasma thrusters[D].Knoxiville,USA:University of Tennessee,2000.
[7] Guang Lin, George Em Karniadakis.High-order modeling of micro-pulsed plasma thrusters[R]. AIAA 2002-2872.
[8] 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:国防科技大学,2007.
[9] 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, 0,1(5):623-628.(YIN Le,ZHOU Jin,MIAO Wan-bo,et al.Simulation of propellant aplation and conduction of pulsed plasma thruster[J].Journal of Propulsion Technology,0,1(5).)
[10] Micci Michael M, Ketsdever Andrew D.Micropropulsion for small spacecraft[M].Reston:American Institute of Aeronautics and Astronautics, 2000:357-358.
[11] 尹乐,周进,缪万波,等.脉冲等离子体推力器的设计评估仿真[J].固体火箭技术, 0,3(4):419-424.
[12] 赵镇南．传热学[M]．北京:高等教育出版社,2008:132-168.
[13] Burton Rodney L, Wilson Michael J, Bushman Stewart S.Energy balance and efficiency of the pulsed plasma thruster[R].AIAA 1998-3808.
[14] Kovitya P.Thermodynamic and transport properties of ablated vapors of PTFE, alumina, perspex, and PVC in the temperature range 5000-30000K [J].IEEE Transaction on Plasma Science,1984, PS-12(1):38-42.
[15] Vondra R J,Thomassen K,Solbes A.Analysis of solid Teflon pulsed plasma thruster[J].Journal of Spacecraft and Rockets,0,7(12):1402-1406.
[16] Albert Solbes,Robert J Vondra.Performance study of a solid fuel-plused electric microthruster[J].Journal of Spacecraft and Rockets,3,0(6):406-410.