| Plasma transport simulation under different conditions and optimization analysis of dual-stage grid ion thruster |
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| 作者姓名： | Yajie HAN Guangqing XIA Bin SUN Chang LU Junjun ZHANG Vladimir A.SAETCHNIKOV |
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| 作者单位： | 1. State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, Dalian University of Technology;2. Key Laboratory of Advanced Technology for Aerospace Vehicles of Liaoning Province, Dalian University of Technology;3. Collaborative Innovation Center of Micro & Nano Satellites of Hebei Province, North China Institute of Aerospace Engineering;4. Physics and Aerospace Technology Department, Belarusian State University |
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| 基金项目： | co-supported by the National Key R & D Program for Intergovernmental International Scientific and Technological Innovation Cooperation,China(No. 2021YFE0116000)；;the National Natural Science Foundation of China (Nos. 12175032, 12102082 and 12275044),the National Natural Science Foundation of China；;the S&T Program of Hebei, China (Nos. YCYZ202201 and 216Z1901G)；;the Science and Technology Project of Hebei Education Department, China (No. ZC2023144)； |
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| 摘 要： | In order to study the extraction and acceleration mechanism of the dual-stage grid, a three-dimensional model based on the Particle-In-Cell/Monte Carlo Collision(PIC/MCC) method is performed. Dual-stage grid ion thruster is a new type of electrostatic ion thruster, which can break through the limitations of traditional gridded ion thrusters, and greatly improve the specific impulse. The high performance also makes the grid sensitive to operating parameters. In this paper,the influence of grid pa...
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| 收稿时间： | 16 June 2022 |
Plasma transport simulation under different conditions and optimization analysis of dual-stage grid ion thruster |
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| Yajie HAN,Guangqing XIA,Bin SUN,Chang LU,Junjun ZHANG,Vladimir A.SAETCHNIKOV.Plasma transport simulation under different conditions and optimization analysis of dual-stage grid ion thruster[J].Chinese Journal of Aeronautics,2023,36(7):388-399. |
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| Institution: | 1. State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, Dalian University of Technology, Dalian 116024, China;2. Key Laboratory of Advanced Technology for Aerospace Vehicles of Liaoning Province, Dalian University of Technology, Dalian 116024, China;3. Collaborative Innovation Center of Micro & Nano Satellites of Hebei Province, North China Institute of Aerospace Engineering, Langfang 065000, China;4. Physics and Aerospace Technology Department, Belarusian State University, Minsk 220030, Belarus |
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| Abstract: | In order to study the extraction and acceleration mechanism of the dual-stage grid, a three-dimensional model based on the Particle-In-Cell/ Monte Carlo Collision (PIC/MCC) method is performed. Dual-stage grid ion thruster is a new type of electrostatic ion thruster, which can break through the limitations of traditional gridded ion thrusters, and greatly improve the specific impulse. The high performance also makes the grid sensitive to operating parameters. In this paper, the influence of grid parameters on xenon ion thruster’s performance in a wide range is systematically simulated, and the optimal operating condition is given. Both the over-focusing of the plume, and the transparency of the screen grid are improved, and the grid corrosion is reduced through simulation optimization. The specific impulse under the given working conditions is 9877.24 s and the thrust is 7.28 mN. Based on the simulation optimization, the limitation of the dual-stage grid is discussed. The grid performs well under high voltage conditions (>3000 V) but not well under low voltage conditions (<2000 V). Finally, since argon is cheaper and more advantageous in future engineering applications, the plasma distribution and grid extraction ability under xenon and argon are analyzed and compared to study the flexibility of the dual-stage grid ion thruster. The simulation results show that a set of optimal parameters is only applicable to the corresponding propellant, which needs to be optimized for different propellant types. |
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| Keywords: | 3D modeling Dual-stage grid Ion thruster PIC/MCC method Plasma simulation |
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