基于CFD的10 cm氙离子推力器阳极推进剂供给方式优化

离子推力器阳极推进剂在放电室内的浓度分布及其变化梯度的设计是放电室放电模式可靠性设计的关键技术之一，直接影响到放电室内推进剂的电离效率及放电稳定性。针对航天器在轨多目标飞行任务对10 cm氙离子推力器的应用需求，为提高10 cm氙离子推力器放电室空腔内阳极推进剂供给的均匀性，实现推进剂利用率的有效提升，运用计算流体动力学（CFD）理论，建立了包括阳极推进剂、进气管和分配环在内的CFD阳极环模型，研究了未发生气体放电情况下，不同供给方式时阳极环内阳极推进剂的压强与流速变化情况。在此基础上，分析了阳极推进剂供给方式对10 cm氙离子推力器放电室空腔内阳极推进剂分布特性的影响作用关系。将优化前后的阳极环在10 cm氙离子推力器中进行了性能对比，结果表明:优化后阳极推进剂电离损耗由277.9 W/A降至241.2 W/A，放电室阳极推进剂利用率由91.7%提升至98.4%，验证了CFD计算结果的正确性与方法的可行性。研究结果为离子推力器放电室拓扑结构设计与优化提供了方法。 

Optimization of anode propellant allocation manner of 10 cm xenon ion thruster based on CFD

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.