氙离子推力器阳极工质分配方式优化

使用两种数值方法研究微尺度下惰性气体的流动现象,验证表明壁面速度滑移条件的N-S（Navier-Stokes）方法能够较好地模拟离子推力器气体分配环内工质流动特性.为了降低氙工质注入放电室过程中气流速度,并改善其周向均匀性,针对现有气体分配环构型提出符合4级环切场离子推力器放电特性的改进方案:增加2级供气通道,进行双侧45°角开孔并增加气孔数目.数值计算表明:结构优化后氙气进入放电室周向均匀性提高37%,气流速度降低32%；推力器装配优化方案气体分配环进行实验,大束流工况下束离子电离能耗自183W/A下降至167W/A,离子推力器放电室性能得到了提高. 

Optimization of anode propellant allocation on xenon ion thruster

Approach of micro-scale similar flow field of inert gas was obtained with two numerical methods.It was verified that the flow characteristics of ion thruster's propellant distributor could be better simulated under first-order velocity slip boundary condition by N-S (Navier-Stokes) method.Based on xenon flow features and discharge characteristics of four-ring-cusp discharge chamber,improvement scheme was proposed for decelerating injection velocity and ameliorating circumferential uniformity of propellant.Dual-stage distributor was utilized and extra amounts of orifices were arranged at 45° on both sides.Calculation results demonstrate that after conducting the improvement scheme,circumferential uniformity of xenon has an amelioration of 37％ while the speed of flow has a decrease of 32％.Furthermore,experimental results illustrate that ion production cost has dropped from 183 W/A to 167 W/A at maximum throttle condition,and performance of discharge chamber has improved.