Abstract
In order to achieve the optimal performance and reliability of the ion thruster in a wide power range, the influence of acceleration grid voltage and anode flow rate on the performance of ion thruster are studied experimentally and theoretically. The results show that in a certain range the ion beam current decreases continuously with the decrease of the absolute value of the accelerating voltage, and then increases suddenly. The electron backstreaming limited voltages in large and small thrust modes are –140 and –115 V, respectively. When the anode flow rate increases, the discharge voltage and discharge loss increase monotonically, and the deceleration current decreases monotonously. Under the power of 300−4850 W, the thrust is 11−188 mN, the specific impulse is 1800−3567 s, and the efficiency ranges from 34% to 67% by adjusting the anode current, grid voltage and working fluid gas flow. The maximum efficiency of thruster reaches 67% at 3000 W. This turning point is critical for thruster design and on-orbit applications. Choosing a reasonable range of working parameters can improve the performance and life of the thruster in application.
Highlights
The results show that in a certain range the ion beam current decreases continuously with the decrease of the absolute value of the accelerating voltage, and then increases suddenly
3) 通过调节阳极电流、栅间电压、工质气体流 量, 推力器在 300—4850 W 功率范围稳定工作, 推 力 11—188 mN, 比冲 1800—3567 s, 效率 34%— 67%, 在 3000 W 时推力器最高效率达到 67%
Summary
1) (兰州理工大学机电工程学院, 兰州 730050) 2) (兰州空间技术物理研究所, 真空技术与物理重点实验室, 兰州 730000) 关键词:离子推力器, 离子束流, 加速电压, 阳极流率 PACS:52.75.Di, 41.75.Ak, 41.85.Ew, 42.65.Jx 我国于 2019 年 12 月由长征五号火箭成功 发射实践二十试验卫星, 兰州空间技术物理研究所 研制的 LIPS-300 双模式离子推力器完成首次在轨
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