| Citation: | SUN M M，GENG H，HU J，et al. Discharge model of divergent magnetic field ion thruster of 10 cm diameter[J]. Journal of Beijing University of Aeronautics and Astronautics，2023，49（9）：2258-2266 （in Chinese） doi: 10.13700/j.bh.1001-5965.2021.0648
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A discharge model of the divergent magnetic field ion thruster (Kaufman thruster) of 10 cm diameter is established with COMSOL multi-physical field coupling software to study the internal discharge process of the thruster and to provide reference for subsequent engineering improvement. The key discharge parameters are obtained and verified through experiments. The calculation results show a magnetic field formed between the upstream and downstream magnetic poles in the discharge chamber with strong divergent characteristics. Due to the orthogonal electric field, the Hall drift of the electrons occur with the magnetic field line as the guiding center. The gas pressure in the discharge chamber is uniformly distributed in the range of 0.1−0.11 Pa, with the neutral atom density in most areas about 1.5×1019 m−3, and the fluid velocity in the range of 0.2−0.9 m/s. The fluid shows obvious characteristics of viscous flow. The peak electron density appears in the cathode outlet region, which is about 8.57×1018 m−3, while the plasma density near the anode wall and the upstream of the screen grid is about 6.8×1017 m−3. The results measured by E×B probe show that the proportion of divalent ions in the total beam ions is 14.1%. The comparison error between the theoretical beam current value of 0.353 mA and the measured beam current value of 0.323 mA is 9%, which is mainly due to the simulation setting and the measurement error. The discharge model established in this paper can provide rapid discharge parameter analysis and reference for optimal design of the thruster.
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