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研究生： 席維廷
Steichen, Valentin
論文名稱： 應用陰極真空電弧觸發裝置於新型脈衝電漿推進器之研發
Development of a new pulsed plasma thruster triggered by a cathodic vacuum arc unit
指導教授： 李約亨
Li, Yueh-Heng
學位類別： 碩士
Master
系所名稱： 工學院 - 航空太空工程學系
Department of Aeronautics & Astronautics
論文出版年： 2020
畢業學年度： 108
語文別： 英文
論文頁數： 72
中文關鍵詞： 真空電弧點火器 、脈衝式電漿推進 、真空電弧推進 、電力推進 、推進器之可靠性
外文關鍵詞： vacuum arc ignitor, pulsed plasma thruster, vacuum arc thruster, electric propulsion, thruster reliability
相關次數： 點閱：160  下載：5 
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    • 衝式電漿推進(簡稱PPT)是一種電力推進系統。主要是通過脈衝電流與自感應磁場之間的相互作用來產生推力，從而使電漿加速。PPT是用於微型衛星中最具前瞻與可行性的電力推進系統之一。由於它成本低，設計簡單，重量輕且消耗的功率少，因此在軌道高度控制和姿態控制方面具有傑出的優勢。如今的研究集中於以下主要方面：推進器的幾何結構，以及推進劑進料系統的優化。這研究重點在於，設計一種新型PPT，並且整合改良新型的進料系統暨點火系統，簡稱為真空電弧點火器（vacuum arc ignitor, VAI）。VAI是使用真空電弧推進器（vacuum arc thruster, VAT）相同的機制產生電漿，進而誘發點火。使用VAI的優勢在於避免後期剝蝕 (late-time ablation)現象的產生，進而降低推進器性能和使用壽命。
    在高真空條件(7×〖10〗^(-5) Torr) 以下，測試該推進器在不同的電極配置條件下的放電現象。結果表明，取決於施加在PPT電極上的電壓，其行為會受到影響。實驗結果顯示，在電壓超過1500V時，點火和第一次放電之間的時間差變得更穩定和一致，並且導致推進器的點火可靠性提高。另外，使用高速攝像機和放電電流測量，一些關於VAI-PPT推進系統在脈衝時間的物理放電過程提出假設，加以解釋。

    Pulsed Plasma Thruster (PPT) is a form of electric propulsion in which the plasma is accelerated by the interaction between pulsed current and self-induced magnetic fields to create thrust. PPT is one of the most promising electric propulsive thrusters for small satellites. As it is a low cost, simple in design, lightweight, and is consuming less power, it has excellent advantages for altitude control and station keeping. Nowadays, research is more focused on main aspects: optimization in geometry and feeding methods. In the frame of this study, a new type of PPT has been designed. This thruster used a new modified feeding and ignition system called a vacuum arc ignitor (VAI). This ignitor creates a plasma using the same mechanism as a vacuum arc thruster (VAT). The advantage of using the VAI is that it avoids a late-time ablation that reduces thruster performance and lifetime.
    The thruster was tested in high vacuum conditions (7×〖10〗^(-5) Torr) with different electrical configurations. The results showed that depending on the voltage applied on the PPT electrodes, and its behavior is affected. It has been shown that over 1500V, the time difference between the ignition and the primary discharge becomes more stable and consistent and leads to an improvement of the thruster reliability. In addition, using a high-speed camera and discharge current measurement, some hypotheses were raised regarding the physical process involved during the VAI−PPT pulse.

    Abstract III 摘要 IV Acknowledgments V Content VI List of figures VII List of Tables X Nomenclature XI List of abbreviations XII Chapter 1: Introduction 1 1.1 Electric Propulsion 1 1.1.1 Electric Propulsion Background 1 1.1.2 Theory about Electric Propulsion 2 1.2 Electric Propulsion, applications, and impact 6 1.3 Electric propulsion and CubeSats 8 1.4 Motivation and Objectives 11 Chapter 2: Literature Review 12 2.1 Plasma principle 12 2.2 Vacuum cathodic arc thruster 14 2.2.2 Basic VCAT theory 14 2.2.3 Operation Principle of VCAT 18 2.3 Pulsed Plasma Thruster 22 2.3.1 Basic Physics of the PPT 22 2.3.2 Operation Principle of S-PPT 25 Chapter 3: Experimental Equipment 27 3.1 Vacuum Chamber and Pump System 27 3.2 Thruster Design 29 3.2.1 Background 29 3.2.2 VAI-PPT final design 30 3.3 Pulse Discharge Circuit 33 3.3.3 Trigerless method 33 3.3.4 Manually triggered circuit 33 3.4 Current and Voltage Measurements 35 3.4.1 Capacitor discharge 35 3.4.2 Discharge Current 36 3.4.3 Ion Current 38 Chapter 4: Results and discussion 40 4.1 Estimation of the electrical parameters 40 4.2 Discharge process 43 4.3 Thruster performance analysis 47 4.3.1 Thruster discharge reliability 47 4.3.2 Thruster discharge quality 49 4.4 Working Principle of the VAI-PPT 50 Chapter 5: Conclusion & Further Work 52 Appendix 54 VAI technical drawing 54 VAI-PPT technical drawing 55 View of the VAI-PPT 56 PYTHON code used for curve fitting 60 PYTHON code used for deltaT calculation 63 Current Probe for High Current 66 Current Probe for Low Current 67 References 69

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