中国物理B ›› 2026, Vol. 35 ›› Issue (3): 35205-035205.doi: 10.1088/1674-1056/adf829
Numerical investigation on performance of electrohydrodynamic thruster with needle-ring electrode
Chun-Yan Wang(王春岩)1, Hu-Lin Huang(黄护林)1,†, Hao Li(李灏)1, Tian-Tian Chen(陈田田)1, and Xi-Jing Hu(胡锡精)2
- 1 Laboratory of Aerospace Entry Descent and Landing Technology, College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China;
2 Beijing Institute of Control and Electronic Technology, Beijing 100038, China
Numerical investigation on performance of electrohydrodynamic thruster with needle-ring electrode
Chun-Yan Wang(王春岩)1, Hu-Lin Huang(黄护林)1,†, Hao Li(李灏)1, Tian-Tian Chen(陈田田)1, and Xi-Jing Hu(胡锡精)2
- 1 Laboratory of Aerospace Entry Descent and Landing Technology, College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China;
2 Beijing Institute of Control and Electronic Technology, Beijing 100038, China
摘要： The electrohydrodynamic (EHD) thruster is a propulsion system characterized by its propellant-free operation. This paper employs a plasma chemical model to systematically investigate three critical parameters affecting EHD propulsion performance: oxygen concentration, secondary electron emission coefficient (SEEC), and voltage polarity. Results show that optimizing the nitrogen-to-oxygen concentration ratio from 4:1 to 5:1 under positive corona discharge enhances the thrust-to-power ratio by 41.3%. Furthermore, increasing the SEEC from 0.001 to 0.01 produces significant performance improvements, with thrust increasing by 34.5% and thrust-to-power ratio surging by 142.2%. Notably, negative corona discharge exhibits substantially reduced efficiency, as the accumulation of positive charges near the emitter electrode induces aerodynamic resistance, resulting in thrust values less than 1% of those achieved in positive discharge configurations.
中图分类号: (Plasma simulation)
- 52.65.-y