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研究生： 陳怡蒨
Chen, Yi-Chien
論文名稱： 以阻抗匹配及代理模型優化離子推進系統
Advanced Optimization of Ion Propulsion via Impedance Matching & Surrogate Modeling
指導教授： 李約亨
Li, Yueh-Heng
學位類別： 碩士
Master
系所名稱： 工學院 - 能源工程國際碩博士學位學程
International Master/Doctoral Degree Program on Energy Engineering
論文出版年： 2022
畢業學年度： 110
語文別： 英文
論文頁數： 145
中文關鍵詞： 電力推進 、離子推進器 、代理模型 、Kriging 模型
外文關鍵詞： Electric propulsion, Ion thruster, RPA (Retarding Potential Analyzer), Surrogate Model, Kriging Model
相關次數： 點閱：46  下載：0 
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    • 隨著5G技術的快速發展，近幾十年來對衛星的需求急劇增加。在這些太空技術中，電力推進系統（Electric Propulsion）被譽為當今太空產業的舵手，將引領吾人探索深空(Deep Space)之秘。作為電力推進家族的一員，離子推進器以其高比衝、長壽命和便於調整體積之特性證實了它的研究價值。雖然人類已開發出多種離子推進器，但對於其設計方法之研究則相對稀少。本研究以射頻電網式離子推進器(RF Gridded Ion Thruster)做為範例，分析其推進器之性能表現以及採用代理模型等數值計算方法來獲得推力性能隨設計參數變化的規律。幾個參數被分類和量化以確定對推力性能的影響。研究結果表明，在4 sccm 之氬氣質量流率、2500 V的加速電網電壓以及40 W 射頻功率下，離子推進器可以實現1.9 mN的推力、1649.5 s的比衝值和 48% 的推力效率，符合設計需求。在點火成功的基礎上，此原型驗證了代理模型優化的有效性，可為往後離子推進器研究提供一些技術指導。

    With the rapid development of 5G technology, the demand for satellites has been increasing drastically in recent decades. Among these space techniques, electric propulsions (EP) are hailed as the helmsman of the space industry that leads us to a place where “the universe” is the limit — deep space exploration. As a member of the EP family, the ion thruster has proved its academic values due to its high specific impulse, enduring lifetime, and adaptable scaling characteristics. While multiple kinds of ion thrusters have been investigated extensively, the scaling design methodology is relatively unexplored. This paper studies the performance of a specific species of an ion thruster: RF gridded ion thruster and focuses on the optimization approaches. Numerical calculation methods such as surrogate modeling are used to obtain the law that the thrust characteristics vary with the design parameters. Several parameters are categorized and quantified to ascertain the influence on the thrust performance. The findings suggest that with the argon mass flow rate of 4 sccm, the acceleration grid voltage of 2500 V, and the RF power of 40 W, the ion thruster can achieve a thrust of 1.9 mN, a specific impulse of 1649.5 s, and a thrust efficiency of 48 %, which meets the design requirements. Based on the ignition success, the prototype verifies the effectiveness of the surrogate modeling, which can be a guideline for further research.

    摘要 I ABSTRACT II 第一章 緒論與文獻回顧 III 第二章 實驗設置與方法 IV 第三章 電漿放電之穩定 V 第四章 推進器優化與實驗結果 VI 第五章 結論 VII 致謝 VIII ACKNOWLEDGEMENTS X CONTENTS XIII LIST OF FIGURES XVIII LIST OF TABLES XXIV NOMENCLATURE XXV CHAPTER 1 INTRODUCTION & LITERATURE REVIEW 1-1 PREFACE 1 1-2 INTRODUCTION TO ELECTRIC PROPULSIONS 2 1-2-1 ElectroThermal Propulsions 3 1-2-2 ElectroStatic Propulsions 7 1-2-3 ElectroMagnetic Propulsions 9 1-2-4 The Optimization of Electric Propulsions 11 1-3 LITERATURE REVIEW OF ION THRUSTERS 12 1-3-1 Development of Ion Thrusters 12 1-3-2 Plasma Sources 14 1-3-3 Ion Optics 20 1-3-4 The Current Research of Ion Thrusters 26 1-4 OPTIMIZATION METHODS 27 1-4-1 The Optimization of Ion Thrusters 27 1-4-2 Important Parameters & Metrics for Performance 30 1-4-3 Surrogate-Based Analysis & Optimization (SBAO) 33 1-5 MOTIVATION & PURPOSE 35 1-6 DISSERTATION STRUCTURE 36 CHAPTER 2 EXPERIMENTAL SETUP & METHODOLOGY 2-1 PLASMA BEHAVIORS & ELECTRIC DISCHARGE REGIME 37 2-2 ION THRUSTER SYSTEM 41 2-2-1 Vacuum Chamber & Propellant Feeding System 42 2-2-2 RF Power System & Impedance Matching Mechanism 44 2-2-3 Discharge Chamber & Coils 46 2-2-4 Acceleration Grids & Neutralizer 46 2-3 DIAGNOSTIC SYSTEMS: LANGMUIR PROBE & RETARDING POTENTIAL ANALYZER (RPA)48 2-3-1 Theory of Langmuir Probes 48 2-3-2 Double Probe Measurement 54 2-3-3 Theory of RPA 55 2-3-4 Design of Gridless RPA 62 2-3-5 Comparisons of Double Probe & RPA 66 2-4 OPTIMIZATION METHOD 67 2-4-1 Kriging Model ─ Gaussian Process 69 2-4-2 Infill Criterion 70 2-5 OPERATIONAL PROCEDURE 71 CHAPTER 3 STABILIZATION OF PLASMA DISCHARGE 3-1 FUNDAMENTAL OF INDUCTIVELY COUPLED PLASMA 72 3-2 IGNITION PROBLEM OF THE THRUSTER 74 3-3 POWER TRANSMISSION APPROACH 74 3-3-1 Impedance Matching Circuit 74 3-3-2 RF ElectroMagnetic Model 78 3-3-3 Impedance of the Plasma alone 84 3-3-4 RF Transformer Model 86 3-3-5 Power Transfer Efficiency 89 3-4 SOLENOID DESIGN 89 3-4-1 Theoretical values of the coil inductance 89 3-4-2 Impedance Measurement of the coils 92 3-5 PRESSURE ACCUMULATION PROBLEM FROM THE CHAMBER 94 3-5-1 Original Discharge Chamber 95 3-5-2 Principle of Discharge Chamber Design 96 3-5-3 New Design & Testing 101 3-6 SUMMARY OF POSSIBLE OPTIMIZATION PARAMETERS 105 CHAPTER 4 OPTIMIZATION VIA SURROGATE MODELING 4-1 SAMPLING METHODS 106 4-1-1 Random Sampling 107 4-1-2 Latin Hypercube Sampling (LHS) 107 4-1-3 Orthogonal Sampling 109 4-2 SCALING LAWS OF RF ION THRUSTERS 110 4-3 OBTAINMENT OF INPUT VALUES 115 4-3-1 Predicament of Thrust Measurement 117 4-3-2 Alternative Measurement Approach 117 4-3-3 Estimation of Thruster Performance 118 4-4 SIMULATIONS VIA KRIGING MODEL 120 4-4-1 Kriging Model Construction 121 4-4-2 Kriging Prediction 122 4-4-3 Explanation of Kriging Model 124 4-5 OPTIMIZATION OF ION THRUSTERS 126 4-5-1 Enhancement of the previous study 126 4-5-2 Comparison with the literature 127 CHAPTER 5 CONCLUSIONS AND FUTURE WORK BIBLIOGRAPHY & REFERENCES 132

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