臺灣博碩士論文加值系統

電力推進（Electric Propulsion, EP）通過高速排出電漿（plasma）進而產生推力。通常，電力推進系統是透過電力系統消耗和電離其推進劑，進而產生電漿流動。與傳統的化學推進系統相比，EP具有較高的比衝量，意味著推進劑的燃料轉化率也相對地高。本研究的重點是從設計、製作與實測方面進行真空陰極電弧推進器（Vacuum Cathode Arc Thruster, VCAT）的研究與開發。特徵在於，VCAT系統不需要任何額外的推進劑進料系統，因為此系統的陰極同時作為電極與推進劑。至於點火方面，塗覆於陰極表面上的石墨層中產生微小熱點會誘發焦耳加熱，將石墨昇華進而誘導電漿產生與流動。VCAT系統具有尺寸小、重量輕，與系統簡單的優點，非常適用於微型衛星的推進系統。此外，本研究使用具有電感器儲存電源系統的“無觸發”方法來產生脈衝電漿。這種放電方法可以顯著地降低輸入功率。VCAT的推力主要是由電漿流中金屬離子的高速排氣速度(exhaust velocity)所引發；無疑地，離子密度、離子速度和離子電荷皆為重要的性能參數。另一方面，本研究使用電池代替電源供應器以減少整個VCAT系統的電力處理單元，並通過測量放電電流和電壓之間的變化以估算單位脈衝所需的能量為0.266J，並透過離子檢測器來測量離子流為3.55A，離子速度為23150m/s。最後，根據理論分析，本論文VCAT原型可以達到單發衝量為2.3μN·s，比衝值2360s，其相對的整體效率約為10%。

Electric propulsion system (EP) yields a thrust by expelling plasma with high exhaust speed. In general, the propellant of EP is initially consumed and ionized via electric power system and it provides plasma flow. Compared with conventional chemical propulsion, EP has high specific impulse, and resulting high fuel conversion rate of propellant. This study focused on the development of vacuum cathode arc thruster (VCAT) in design, manufacturing and demonstration aspects. Characteristically, it does not need any additional feeding system of propellant because that cathode electrode doubles as propellant simultaneously. For the ignition process, tiny spots laid on carbon layer coated on the surface of insulator are aimed to induce the plasma generation and plasma flow. With advantages of size and weight reduction and straightforward configuration, VCAT system is appropriate to assemble in the microsatellites. In addition, a ‘trigger less’ method with inductor storage power system was used for generating pulsed plasma. This discharge method can significantly reduce input power. The electric thrust is mainly caused by high exhaust velocities of metal ions in plasma flow; undoubtedly, the ion density, ion velocity, and ion charge are important performance parameters. On the other hand, batteries instead of a power supply were engaged to reduce the entire VCAT energy processing unit. The energy required for a single pulse was estimated to be 0.266J by measuring the change between the discharge current and voltage. The ion current was 3.55A measured by an ion detector, and the resulting ion velocity was 23150m/s. Ultimately, according to the theoretical analysis, the VCAT prototype of this study achieved a single impulse of 2.3μN·s, a specific impulse of 2360s, and an overall efficiency of about 10%.

摘要 I
Abstract II
致謝 III
List of Tables VIII
List of Figures IX
Nomenclature XI
Chapter 1 Introduction 1
1-1 Background 1
1-2 Cubic Satellite Application 2
1-3 Electric Propulsion 4
1-3-1 Electrothermal Type 6
1-3-2 Electrostatic Type 8
1-3-3 Electromagnetic Type 10
1-4 Propulsion System Determination 12
1-5 The Development of VCAT 14
1-6 Motivation and Objective 16
Chapter 2 VCAT Theory 17
2-1 Plasma 17
2-2 Vacuum Cathode Arc Thruster (VCAT) 19
2-3 Basic VCAT Theory 24
2-4 Operation Principle of VCAT 33
Chapter 3 Experimental Equipment and Methods 39
3-1 Vacuum Chamber and Pump System 39
3-1-1 Vacuum System Leak Detection 41
3-2 Pulse Discharge Circuit 46
3-3 Cathode Erosion Rate Measurement 48
3-4 Langmuir Probe 50
3-5 Voltage and Current Measurement 51
3-6 Ion Current Measurement 53
Chapter 4 Concept and Design of VCAT System 55
4-1 Background 55
4-2 Concept of Thruster Design 56
4-2-1 Cathode Material 58
4-3 Concept of Pulse Discharge Circuit Design 59
4-3-1 Triggerless Method 60
4-4 Final Thruster Design 61
4-4-1 Thruster Prototype Design 62
4-4-2 Discharge Mechanism 64
4-5 Final Circuit Design 67
4-5-1 Pulse Discharge Circuit Design 68
4-5-2 Micro Function Generator Design 74
4-5-3 Micro Power Supply 77
Chapter 5 VCAT Demonstration 79
5-1 Vacuum Arc Discharge Process 79
5-2 Circuit Charging and Discharging Process 85
5-3 Plasma Plume Detection 87
5-4 Cathode Erosion Rate and Lifetime 89
5-5 VCAT Performance Analysis 91
Chapter 6 Conclusion and Future Works 95
Reference 98

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