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研究生： 楊宗穎
Yang, Tsung-Ying
論文名稱： 固體推進劑中混摻鐵粉對脈衝式電漿推進器整體性能的影響
Effect of iron powder blending in solid propellant on the overall performance of pulsed plasma
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： 2025
畢業學年度： 113
語文別： 英文
論文頁數： 113
中文關鍵詞： 電力推進器 、脈衝式電漿推進器 、金屬複合聚合物 、PMMA混摻鐵粉 、效率 、推力功率比
外文關鍵詞： Electric propulsion, Pulsed plasma thruster, Metal-composite polymer, PMMA@Fe, Efficiency, Thrust-to-power ratio
ORCID： https://orcid.org/0009-0004-6504-9371
相關次數： 點閱：34  下載：2 
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    • 脈衝電漿推進器（PPT）因其小型化、簡單性及精確推力生成能力，廣泛應用於立方衛星。然而，其低效率及推力功率比限制了更廣泛的採用。本研究提出一種新型 PMMA 金屬複合聚合物推進劑（PMMA@Fe），以摻雜鐵粉作為替代傳統 PTFE 推進劑的方案。合成並評估了鐵粉濃度範圍為 5 wt% 至 20 wt% 的 PMMA@Fe 樣品。結果顯示，鐵粉的添加降低了電漿阻抗並提高放電電流，相較於純 PMMA，其脈衝推力（impulse bit）提升了 62.5%（從 80.3 μNs 增至 131.9 μNs），推力功率比提升了 63.5%（從 17.8 μN/J 增至 29.3 μN/J）。 材料分析顯示，PMMA的燒蝕速率從純 PMMA 的 4.5 μg/shot 增至 PMMA@5 wt% Fe 的 8.1 μg/shot，並在更高濃度下趨於平穩。電漿羽流分析表明，隨著鐵含量增加，電漿生成量增幅達 50%，PMMA 分解物的光學發射強度提高了 40%。儘管性能有所提升，但高鐵含量（≥20 wt%）導致不規則放電及碳和金屬沉積，限制了推進器的使用壽命至 6000 次放電。本研究結果顯示PMMA@15 wt%Fe 為最佳配方，達到 19.6% 的推力效率及 1,426 s 的比衝，同時保持結構完整性。這些研究結果表明，PMMA@Fe 在提升 PPT 效能方面具有顯著潛力，可有效應對立方衛星應用中的效率及耐久性挑戰。

    Pulsed plasma thruster (PPT) is extensively utilized in CubeSats due to their compact size, simplicity, and precise thrust generation capabilities. However, their limited efficiency and thrust-to-power ratio constrain broader adoption. This study presents a novel PMMA-based metal-composite polymer propellant (PMMA@Fe) doped with iron powder as an alternative to conventional PTFE propellants. PMMA@Fe samples with iron powder concentrations ranging from 5 wt% to 20 wt% were synthesized and evaluated. Results show that the addition of iron powder reduced plasma impedance and increased discharge currents, leading to a 62.5% improvement in impulse bit (from 80.3 μNs to 131.9 μNs) and a 63.5% increase in the thrust-to-power ratio (from 17.8 μN/J to 29.3 μN/J) compared to pure PMMA.
    Material analysis revealed an increase in the ablation rate from 4.5 μg/shot (pure PMMA) to 8.1 μg/shot (5 wt% Fe), plateauing at higher concentrations. Plasma plume analysis indicated a 50% rise in plasma generation and a 40% enhancement in optical emission intensity with increasing iron content. Despite these performance improvements, higher iron concentrations (≥20 wt%) caused irregular discharges and carbon-metal deposition, limiting the thruster lifespan to 6,000 discharges.
    The optimal composition was identified as PMMA@15 wt%Fe, achieving 19.6% thrust efficiency and a specific impulse of 1,426 s while maintaining structural integrity. These findings demonstrate the potential of PMMA@Fe to significantly enhance PPT performance, addressing the challenges of efficiency and durability for CubeSat applications.

    摘要 I Abstract II 誌謝 IV Content VI List of tables IX List of figures X Nomenclature XIV CHAPTER 1 Introduction 1 1-1 Background 1 1-2 Propulsion systems for satellites 4 1-2-1 Chemical propulsion 5 1-2-2 Electric propulsion 6 1-3 Development of pulsed plasma thruster 11 1-4 Pulsed plasma thruster propellants 13 1-5 Motivation and Objective 14 CHAPTER 2 Theory of pulsed plasma thruster 18 2-1 Mechanism of plasma acceleration 18 2-1-1 Electromagnetic force 18 2-1-2 Electrothermal force 21 2-2 Propulsion performance parameters 23 CHAPTER 3 Materials and Methods 25 3-1 Experimental setup 25 3-1-1 PMMA@Fe preparation 25 3-1-2 Experimental apparatus 29 3-1-3 Experimental method 32 3-2 Vacuum system 34 3-3 Analysis equipment 35 3-3-1 Dielectric Property Analysis 35 3-3-2 SEM-EDS analysis 37 3-3-3 Micro-CT analysis 38 3-3-4 Faraday cup 39 3-4 Circuit design and optimization 40 3-4-1 High-voltage discharge circuit design 40 3-4-2 Optimization of inductive energy storage ignition circuit 46 3-5 Thruster design 55 CHAPTER 4 Result and discussion 57 4-1 Characterization of the PMMA@Fe 57 4-1-1 SEM-EDS analysis 57 4-1-2 Micro-CT analysis 63 4-2 Discharge characteristics of PPT with PMMA@Fe 66 4-3 Average ablation rate of the different experimental conditions (case 1~5) 71 4-4 Average impulse bit of the different experimental conditions (case 1~5) 72 4-5 Faraday cup with the different experimental conditions (case 1~5) 73 4-6 SEM-EDS analysis of PMMA@Fe after ablation 78 4-7 Optical emission spectrum 81 4-8 Thruster performance 85 CHAPTER 5 Conclusion and Future Work 89 5-1 Conclusion 89 5-2 Future work 90 Reference 92

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