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研究生： 王唯丞
Wang, Wei-Cheng
論文名稱： 百瓦級自製氬氣霍爾推進器之研製
Development of hundred-watt-class indigenous Hall effect thruster
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： 2025
畢業學年度： 113
語文別： 英文
論文頁數： 133
中文關鍵詞： 電力推進 、霍爾推進器 、中空陰極 、法拉第探針 、旋轉平台
外文關鍵詞： Electric propulsion, Hall thruster, Hollow cathode, Faraday probe, Vacuum Rotating system
ORCID： https://orcid.org/0009-0009-6696-4666
ResearchGate： https://www.researchgate.net/profile/Wei-Cheng-Wang-6?ev=hdr_xprf
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    • 隨著科技持續進步，太空產業展現出高度的戰略價值與商業潛力。其中，衛星任務的成敗關鍵之一即在於推進系統的可靠性與效能。推進系統不僅可用於軌道轉移與姿態控制，支援通訊、遙測與觀測等任務，亦能於任務結束後執行離軌操作，以降低太空垃圾對軌道環境之衝擊。現行太空推進技術主要分為化學推進與電力推進兩大類。前者具備高推力，適用於火箭發射與快速變軌；後者則以高效率與高比衝為優勢，特別適合長時間運作且阻力極小之太空環境，已逐漸成為新一代衛星推進系統的主流選項。霍爾推進器作為靜電式電力推進技術的一種，具有良好的推力功率比與操作穩定性，結構簡單、壽命長，現已廣泛應用於低軌衛星任務。然而，目前台灣在電力推進系統的研發尚屬初期階段，缺乏完整自主開發經驗。為提升技術自主性、降低成本並強化本土太空產業鏈，有必要發展具在地化製造能力之電力推進系統。
    本研究針對百瓦級霍爾推進器進行設計與實驗驗證，目標為建立適用於小型衛星之低功率電力推進技術。推進器採用永久磁鐵取代傳統電磁線圈以降低功耗與熱負載，並選用價格低廉、來源穩定的氬氣作為推進劑，其每公斤成本僅為氙氣的1%以內。設計上參考商用SPT-100推進器參數，並根據理想縮放理論進行ZAP-25推進器幾何與磁路設計，搭配磁場模擬優化結構配置與陽極設計。
    實驗方面，推進器配合自製無加熱中空陰極完成點火，並利用旋轉平台搭配法拉第探針進行羽流掃描，以量測總離子電流並推算推力性能。性能測試涵蓋不同質量流率（20–30 sccm）、輸入功率（85–115 W）與磁場強度（210 G 與 320 G），以探討操作參數對性能之影響。實驗結果顯示，在114.5 W、30 sccm、低磁場條件下可獲得最大推力1.87 mN；而於112.5 W、20 sccm、低磁場條件下則達到最高比衝226 s。值得注意的是，相較於氙氣，氬氣推進劑於磁場強度變化下展現不同趨勢，當磁場增加至320 G時反而導致性能下降，推測可能因異常電子擴散效應加劇，而氬氣較適合於經典電子擴散主導區域內運作。
    目前氬氣於低功率霍爾推進器之應用相關實驗參數仍相對有限，期盼本研究能對永久磁鐵應用於電力推進系統，以及氬氣霍爾推進器相關領域提供初步參考與實驗依據。實驗結果顯示，透過永久磁鐵結合氬氣推進劑之配置，確實可實現穩定放電，並展現低成本與小型化等潛在優勢。

    Space propulsion systems are vital for satellite missions, including orbit maintenance, maneuvering, and deorbiting. Chemical propulsion delivers high thrust, while electric propulsion offers better efficiency and specific impulse, making it ideal for long-duration missions. Hall thrusters, known for their good thrust-to-power ratio and simple structure, are widely used in low Earth orbit. In Taiwan, electric propulsion development is still emerging. This study designs and tests a 100-watt-class Hall thruster for small satellites, using permanent magnets to reduce power and heat, and argon as a low-cost, abundant propellant. The design is based on the SPT-100 model and optimized using magnetic field simulations.
    Experiments used argon heaterless hollow cathode and a rotating system with Faraday probe for plume diagnostics. Tests covered flow rates of 20–30 sccm, power levels of 85–115 W, and magnetic fields of 210 G and 320 G. The thruster reached a maximum thrust of 1.87 mN and a peak specific impulse of 226 s at lower magnetic field strength. Performance dropped with stronger magnetic fields, likely due to increased anomalous electron diffusion.
    This study confirms the feasibility of using argon and permanent magnets for low-cost electric propulsion in small satellites.

    中文摘要 I ABSTRACT III LIST OF TABLES VII LIST OF FIGURES VIII NOMENCLATURE X Chapter 1. INTRODUCTION 1 1.1 Preface 1 1.2 Space propulsion system 2 1.2.1 Different types of electric propulsion 3 1.2.2 Electric propulsion performance metrics 7 1.3 Features and principles of Hall thrusters 8 1.3.1 Configuration & operating principles of Hall thrusters 8 1.3.2 Advantages & Disadvantages of Hall thrusters 10 1.4 Motivation & Objective 13 1.4.1 Motivation 13 1.4.2 Objective 14 Chapter 2. LITERATURE REVIEW 15 2.1 Hall thruster physics 15 2.1.1 Ionization & Acceleration process 15 2.1.2 Voltage & Current distribution 19 2.1.3 Hall thruster propellant selection 21 2.2 Hall thruster design methodology 25 2.2.1 Ideal Scaling Principles 26 2.2.2 Propellant Ionization & Scaling of the Ionization Layer 28 2.2.3 Electron Confinement & Magnetic Field Optimization 29 2.2.4 Power Losses and Geometric Considerations 32 2.2.5 Summary of scaling law 33 2.3 Electron source for Hall thruster 34 2.3.1 Traditional Hollow cathode 34 2.3.2 Heaterless hollow cathode 36 2.4 Faraday probe 38 2.4.1 Basic principle of Faraday probe 39 2.4.2 Faraday probe measurement at Hall thruster plume 41 Chapter 3. DESIGN of ZAP-25 HALL THRUSTER 44 3.1 Thrust power & Parameter decision 44 3.1.1 Nominal power decision 44 3.1.2 Critical parameters decision 45 3.2 Magnetic circuit design 47 3.2.1 Magnetic circuit components 47 3.2.2 Magnetic field intensity tuning & Magnet Mounting 51 3.3 Anode & Propellant Distribution Design 56 3.3.1 Anode injection pressure estimation & Flow connection 57 3.3.2 Electrical insulation & Power connection 60 3.4 Final design 64 Chapter 4. EXPERIMENTAL SETUP 68 4.1 Instrumentation 68 4.1.1 Vacuum chamber 70 4.1.2 Propellant feeding system 71 4.1.3 Power supplies 73 4.1.4 Measurement devices 74 4.2 Heaterless hollow cathode 76 4.3 Plume scanning system 78 4.3.1 Rotating system 78 4.3.2 Faraday probe 80 Chapter 5. RESULTS & DISCUSSION 84 5.1 Experimental results & analysis 84 5.1.1 Performance analysis in different flow rate 85 5.1.2 Performance analysis in different power levels 92 5.1.3 Performance analysis in different magnetic intensity 95 5.2 Comparative study of thrust performance 100 Chapter 6. CONCLUSION 104 Chapter 7. FUTURE WORK 106 REFERENCE 109 APPENDIX 114 A. Matlab code for performance calculation 114 B. ZAP-25 Hall thruster ignition procedure 117

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