《Table 1.Flow properties of LIPS-200 ion tchruster used in simulation cases.》
本系列图表出处文件名:随高清版一同展现
《Three-dimensional particle simulation of ion thruster plume flows with EX-PWS》
The flow rate and the temperature are obtained from the actual situation during the experiment and the velocity is calculated according to the grid voltage(~1000 V).The thruster exit plane is the entrance of xenon atoms,single charged ions and double charged ions.Particles are ejected following the distribution shown in equation(2).Otherwise,the mass flow rate of the neutralizer cathode is about0.13 mg s-1,and the coupling voltage is about 20 V(17–23 V).The cathode primarily affects the near-field around the thruster exit on the plane including the axes of cathode and thruster,and has little effect on the far field.Accordingly,in the current study,we neglect the effect from the cathode.Moreover,the thruster exit is supposed to be electronically grounded in this study.
图表编号 | XD0015685300 严禁用于非法目的 |
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绘制时间 | 2018.10.01 |
作者 | 郑鸿儒、蔡国飙、王虹玥、刘立辉、贺碧蛟 |
绘制单位 | School of Astronautics, Beihang University、School of Astronautics, Beihang University、Beijing Institute of Aerospace Testing Technology、School of Astronautics, Beihang University、School of Astronautics, Beihang University |
更多格式 | 高清、无水印(增值服务) |