本論文致力於發展具有不同的電極擴張角度，以及非對稱角度之微型脈衝式電漿推進器（簡稱PPT），選擇四個不同的電極夾角和非對稱配置設置，以檢測其電極結構參數對於推進器性能和可靠性之影響。
與傳統化學推進系統相比，電力推進系統使用高速排出的電漿。首先，電力推進系統的推力是由電漿流中，離子的高排氣速度所產生。微型脈衝式電漿推進器是太空工程中仍在使用的最古老之推進技術之一，及具有簡單性和低成本的特徵，使其對於微型衛星的電力推進系統發展具有吸引力。此外，PPT也吸引青年創業的太空公司和高等教育機構參與，促進到當前太空產業發展。
近年來，PPT在設計、製造和示範方面，已完成在電力推進系統應用於立方衛星方面進行相關研究與技術發展。 PPT的原型機設計先前已經完成，本研究主要通過可拆卸和可更換的部件對推進器的推力性能進行改進。通過高速相機的使用已經觀察到並解釋未解決的電漿放電現象，並且提出假設模型。此外，採用田口方法來檢查設計參數對推進器性能和可靠性的影響。

This master thesis focuses on the development of a pulsed plasma thruster (PPT in short) using an electrode with the variation of electrode angles and asymmetric angles. Four different electrode angles and asymmetric configurations set-ups were selected and examined, and it concludes the influence on the performance and reliability of the thruster.
Compared to the conventional chemical propulsion systems, electric propulsion uses expelling plasma with high speed. Primarily, the electric thrust is generated by high exhaust velocities of ions in the plasma flow. Pulsed Plasma Thruster is one of the oldest propulsion technologies still used in the space industries. Their features relevant to the simplicity and low cost make them very attractive for the electric propulsion development of miniature satellites. In addition, PPTs have drawn increasing attention for young start-up space companies and universities to get involved in the prevailing space industries.
The PPT-relevant researches had been undertaken in the facets of the design, manufacturing, and demonstration of the PPT for Cube satellites in years. The original design of the PPT had been made previously, and then the future improvement can be implemented to the thruster, with detachable and replaceable parts. An unresolved phenomenon has been observed and elucidated by employing the high-speed camera, and hypothetical solutions have been addressed. In addition, the Taguchi method was employed to scrutinize the effect of the design parameter on the performance and reliability of the thruster.

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