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离子推力器羽流热效应仿真分析

张建华 李晶华 尤凤仪 郑鸿儒

张建华, 李晶华, 尤凤仪, 等 . 离子推力器羽流热效应仿真分析[J]. 北京航空航天大学学报, 2018, 44(10): 2028-2034. doi: 10.13700/j.bh.1001-5965.2017.0802
引用本文: 张建华, 李晶华, 尤凤仪, 等 . 离子推力器羽流热效应仿真分析[J]. 北京航空航天大学学报, 2018, 44(10): 2028-2034. doi: 10.13700/j.bh.1001-5965.2017.0802
ZHANG Jianhua, LI Jinghua, YOU Fengyi, et al. Simulation analysis of ion thruster plume thermal effect[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2028-2034. doi: 10.13700/j.bh.1001-5965.2017.0802(in Chinese)
Citation: ZHANG Jianhua, LI Jinghua, YOU Fengyi, et al. Simulation analysis of ion thruster plume thermal effect[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2028-2034. doi: 10.13700/j.bh.1001-5965.2017.0802(in Chinese)

离子推力器羽流热效应仿真分析

doi: 10.13700/j.bh.1001-5965.2017.0802
详细信息
    作者简介:

    张建华  男, 博士, 副研究员。主要研究方向:航空宇航推进理论与技术、稀薄气体动力学、火箭发动机流场计算及测试

    通讯作者:

    张建华, E-mail:zjh@buaa.edu.cn

  • 中图分类号: V439

Simulation analysis of ion thruster plume thermal effect

More Information
  • 摘要:

    离子推力器工作时向外喷出的羽流与航天器表面碰撞,会引起敏感材料热变形等热效应,严重时会导致航天任务失败。针对兰州空间技术物理研究所研制的LIPS-200型离子推力器羽流热效应进行了仿真分析。仿真中,使用粒子网格(PIC)方法处理等离子体运动,使用直接模拟蒙特卡罗(DSMC)方法处理粒子间碰撞,使用Maxwell模型处理粒子与壁面的能量交换,对电推进羽流热效应测量中的部分测点进行了数值模拟。结果表明,仿真结果与实验数据符合较好,离子推力器出口轴线上滞止热流仿真值与实验测量值误差小于17.0%。此外,热流计对流场的影响主要集中在热流计附近0.1 m范围内,对整体流场影响较小。

     

  • 图 1  离子推力器羽流热效应测量系统示意图

    Figure 1.  Schematic diagram of ion thruster plume thermal effect measurement system

    图 2  两种热流传感器实物图

    Figure 2.  Photo of two kinds of heat flow sensor

    图 3  计算域示意图

    Figure 3.  Schematic diagram of computational domain

    图 4  推力器与模拟热流计相对位置示意图

    Figure 4.  Schematic diagram of relative position of thruster and simulated heat flow meter

    图 5  羽流场电流密度仿真与实验对比

    Figure 5.  Comparison of current density in plume flow field between simulation and experiment

    图 6  轴向位置热效应实验和仿真对比

    Figure 6.  Comparison of thermal effect in axial direction between simulation and experiment

    图 7  距离推力器出口0.5 m和0.9 m处径向热流对比

    Figure 7.  Comparison of radial heat flow at 0.5 m and 0.9 m from thruster exit

    图 8  距离推力器出口0.9 m处放置热流计时的一价Xe离子和Xe原子分布

    Figure 8.  Number density distribution of Xe atom and monovalent xenon ion when heat flow meter is located at 0.9 m away from thruster exit

    图 9  距离推力器出口0.9 m处放置热流计时的一价Xe离子、Xe原子及无热流计时数密度对比

    Figure 9.  Comparison of xenon atom and monovalent xenon ion number density distribution on axis with or without heat folw meter located at 0.9 m away from thruster exit

    表  1  LIPS-200型离子推力器仿真基本参数

    Table  1.   Basic parameters of LIPS-200 ion thruster simulation

    粒子种类 流率/s-1 温度/K 速度/(m·s-1)
    Xe 5.69×1017 300 325
    Xe+ 4.609×1018 46400 39000
    Xe++ 5.12×1017 46400 55154
    下载: 导出CSV
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出版历程
  • 收稿日期:  2017-12-25
  • 录用日期:  2018-01-05
  • 刊出日期:  2018-10-20

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