Comparative Study of Two Types of Cusp Field Ion Thruster

被引：0
|
作者：
Zhao Y.-D. [1 ]
Li J.-P. [1 ]
Zhang T.-P. [1 ]
Jiang H.-C. [1 ]
Wang L. [1 ]
Guo D.-Z. [1 ]
Yang W. [1 ]
机构：
[1] Science and Technology on Vacuum Technology and Physics Laboratory, Lanzhou Institute of Physics, Lanzhou
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 11期
关键词：
Cylindrical-cusp field; Efficiency; Ion thruster; Ring-cusp field; Uniformity of beam current density;
D O I：
10.13675/j.cnki.tjjs.200019
中图分类号：
学科分类号：
摘要：
To further advance the performance and reliability of ion thruster, the advantage and disadvantage of two types of cusp field ion thruster were comparativly studied based on both a diameter 30cm cylindrical-cusp field ion thruster (LIPS-300Z) and a diameter 30cm ring-cusp field ion thruster (LIPS-300H). Firstly, the principle of two types of cusp field was analyzed, and their difference was summarized. Then, the uniformity of beam current density, the discharge efficiency and the lifetime were evaluated and analyzed. Compared to the experimental results of the LIPS-300Z, the maximum beam current density of LIPS-300H at the 3kW and 5kW mode was decreased by 25% and 19%, and its discharge voltage was reduced by 7.8V and 6.2V, while the discharge loss of the LIPS-300H at two modes increased by 31W/A and 42W/A, respectively. In addition, the lifetime of screen grid of LIPS-300H at the 3kW and 5kW mode was 7.7 times and 4.2 times as long as LIPS-300Z. The results indicated that LIPS-300Z had a low discharge loss, but its uniformity of beam current density was worse, and the discharge voltage and the ratio of doubly-to-singly charged ions in beam were all high. Therefore, the lifetime and reliability of LIPS-300H were better than those of LIPS-300Z. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.
引用
收藏
页码：2633 / 2640
页数：7
相关论文
共 31 条
  • [1] Clark S, Randall P, Lewis R, Et al., BepiColombo-Solar Electric Propulsion System Test and Qualification Approach
  • [2] Wallace N C, Mundy D H, Fearn D G, Et al., Evaluation of the Performance of the T6 Ion Thruster
  • [3] Randall P N, Lewis R A, Clark S D, Et al., BepiColombo-MEPS Commissioning Activities and T6 Ion Thruster Performance During Early Mission Operations
  • [4] Rawlin V K, Sovey J S, John H A., An Ion Propulsion System for NASA's Deep Space Missions
  • [5] Brophy J R, Mareucei M G, Ganapathi C B, The Ion Propulsion System For Dawn
  • [6] Shastry R, Herman A D, Soulas G C, Et al., Status of NASA's Evolutionary Xenon Thruster (NEXT) Long-Duration Test as of 50000h and 900kg Throughput
  • [7] Shastry R, Herman A D., Soulas G C, Et al., End-of-Test Performance and Wear Characterization of NASA's Evolutionary Xenon Thruster (NEXT) Long-Duration Test
  • [8] Kitamura S, Miyazaki K, Hayakawa Y, Et al., Performance Improvement of 150mN Xenon Ion Thrusters, Acta Astronautica, 52, pp. 11-20, (2003)
  • [9] Zhao Yide, Zhang Tianping, Wu Zonghai, Et al., Performance Evaluation of the 30cm Ring-cusps Ion Thruster, Shanghai: 7th CSA/IAA Conference on Advanced Space Technology, (2017)
  • [10] ZHAO Yi-de, ZHANG Tian-ping, HUANG Yong-jie, Et al., Experimental Study of 40cm Ion Thruster over a Wide Range of Input Power, Journal of Propulsion Technology, 39, 4, pp. 942-947, (2018)
1234