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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。
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关键词:
- 电推进 /
- 羽流 /
- 热效应 /
- PIC-DSMC方法 /
- 数值模拟
Abstract:The plume ejected from a working ion thruster collides with the surface of spacecraft, which may cause thermal effects such as thermal deformation of the sensitive material and lead to the failure of the space mission in severe cases. In this paper, the plume thermal effect of LIPS-200 ion thruster developed by Lanzhou Institute of Space Physics was simulated. The particle in cell (PIC) method is employed to process the plasma motion, the direct simulation Monte Carlo (DSMC) method is employed to deal with the collision between particles, and the Maxwell model is employed to deal with the energy exchange between the particle and the surface. Part of the measuring points in the experiment of electric propulsion plume thermal effect was numerically simulated. The results show that the simulation results are in good agreement with the experimental data. The error between simulation results and experimental data of the stagnation heat flow on the outlet axis of the thruster is less than 17.0%. In addition, the influence of the heat flow meter on the flow field is mainly concentrated within 0.1 m near the heat flow meter, which has little impact on the overall flow field.
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Key words:
- electric propulsion /
- plume /
- thermal effect /
- PIC-DSMC method /
- numerical simulation
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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 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 
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