Project Title: 應用於立方衛星之微型電漿推進器的設計、測試與應用
Role: 計畫主持人 (PI)
Duration: 2016.08-2019.07
Funding Program: 科技部優秀年輕學者研究計畫
Grant Number: MOST105-2628-E-006-005-MY3
Funding Amount: NTD$3,471,000
Abstract: 本計畫為期三年，針對立方衛星發展微型電漿推進器，以脈衝式電漿推進器（PPT）和真空陰極電弧推進器為重點。第一年發展 PPT 系統，包含推進劑、陰極、陽極與電力系統：放電電弧使固態推進劑氣化並電離，放電電路產生的感應磁場以勞倫茲力加速帶電粒子而產生推力。固態推進劑可大幅簡化供料系統並降低重量與體積，適合微型立方衛星。
Publication:
● Effect of Electrode Angle on Pulsed Plasma Thruster Performance. Journal of Aeronautics, Astronautics and Aviation, vol. 53(3), pp. 353-368, 2021.
● Design and demonstration of micro-scale vacuum cathode arc thruster with inductive energy storage circuit. Acta Astronautica, vol. 172, pp. 33-46, 2020.
● Effects of a microwave-induced corona discharge plasma on premixed methane-air flames. Energy, vol. 188, pp. 116007, 2019.
● Effect of voltage on second-stage electrodes of dual-stage solid propellant pulsed plasma thruster. Vacuum, vol. 167, pp. 103-112, 2019.
● Taguchi optimization of solar thermal and heat pump combisystems under five distinct climatic conditions. Applied Thermal Engineering, vol. 133, pp. 283-297, 2018.
● Power Generation Performance of Hydrogen-fueled Micro Thermophotovoltaic Reactor. International Journal of Hydrogen Energy, vol. 43, pp. 1459-1469, 2018.
● Plasma behavior in a solid-fed pulsed plasma thruster. Journal of Aeronautics, Astronautics and Aviation, vol. 51(1), pp. 031-042, 2018.
Key Findings:
● 固態推進劑脈衝電漿推進器在6.25 J下衝量位元達84 μN·s;三重朗繆探針量得距噴嘴30 mm處電子密度8×10^20 m^-3、電子峰值速度25 km/s。
● 雙階段PPT在25 J下最大總衝量位元為72.35 μN·s,提高第二階段能量可增加總衝量。
● 以電感儲能電路驅動的真空陰極電弧推進器,每脈衝約需0.266 J,離子電流3.55 A,離子速度23,150 m/s。
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