| Citation: | HU Jing, YANG Fuquan, GUO Dezhou, et al. Optimization of anode propellant allocation manner of 10 cm xenon ion thruster based on CFD[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(8): 1476-1484. doi: 10.13700/j.bh.1001-5965.2019.0484(in Chinese)
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The concentration distribution of anode propellant in discharge chamber and its gradient design is one of the most important techniques in discharging mode reliability design, and it directly influences the ionization efficiency and discharge stability of anode propellant. Aimed at the application requirement of multi-objective attitude and orbit control of spacecraft for 10 cm xenon ion thruster, by using the Computational Fluid Dynamics (CFD) method, the CFD model for analyzing the propellant allocation manner is established, which consists of the propellant, the inner tube and the distribution ring. The pressure and velocity distribution rules of anode-ring propellant in different allocation manners were studied without discharge progress to ameliorate circumferential uniformity of propellant in 10 cm xenon ion thruster discharge chamber and improve its utilization efficiency. On this basis, the influences of anode propellant allocation manner on the propellant distribution characteristics in discharge chamber were analyzed. And the performance of anode-ring before and after optimization in 10 cm xenon ion thruster are compared. The results show that after the improvement of the anode propellant allocation manner, the ion production cost drops from 277.9 W/A to 241.2 W/A, and the propellant utilization efficiency in discharge chamber increases from 91.7% to 98.4%, which verify the correctness of CFD calculation results and the feasibility of the CFD method. The results of this research will certainly provide method for the topological structure design and optimization of the discharge chamber of ion thruster.
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