| 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)
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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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