本論文研究強調實作創新，為國內首次自主研發微衛星用過氧化氫微推進器，並自行開發確實掌握自過氧化氫推進燃料、分解觸媒以至於微推進器設計與測試等相關關鍵材料與技術，完全自製完成一示範原型100 mN 過氧化氫微推進系統，經測試符合設計目標與需求。
　　目前衛星微型化雖然有助於降低成本與風險，相對的需要更精準的微推力姿態控制系統(Attitude Control System)，這方面的研究在過去相對的很缺乏。過氧化氫具有適當的比衝值且燃料取得成本低，對環境衝擊小的優點。本研究針對50kg級微型太空飛行器的姿態控制需求，使用自行開發的濃度92% 的高性能過氧化氫(High-Test Peroxide, HTP)微推進劑設計單推進劑(Monopropellant)微推進器，目標推力等級約100 mN。
　　本研究針對過氧化氫分解觸媒選擇與製備以及銀觸媒床系統因尺寸縮小造成的性能減退與工程技術難度，包括因相對熱損提高造成分解溫度比絕熱分解溫度低而液氣兩相造成觸媒分解效率下降，噴嘴的尺寸與邊界層，微推力測試設備等問題，以各種特殊工程技術與設計加以克服以符合目標需求。
　　設計過程藉由理論分析與初步實驗，獲得過氧化氫微推進器適合的操作參數，配合地面測試得到相關性能參數，建立設計點參數與性能估算以及設計程序。設計微推進器原型內填充銀觸媒0.7g，整體體積0.9cm3，重量5.8g。實驗結果發現使用91.5% 過氧化氫流量0.18 g/s，其分解效率超過80%，分解溫度最高可達約890 K，觸媒床壓力5.86 bar。地面測試量測推力得182 mN，比衝值103 s，推估在真空中比衝值可達150 s以上，符合設計目標與需求。

　In this study, indigenous technology development of an advanced HTP (High-Test Hydrogen Peroxide) microthruster system for micro-spacecrafts is presented. For the first time in this country, the key materials, components and techniques of a HTP thruster system, including the HTP monopropellant, decomposing catalysts, and system and component design and test techniques, are completely and indigenously developed. A demonstrating prototype of a 100 mN HTP microthruster system is designed, manufactured and tested, and the test results show that the performance of the microthruster can meet the design goal and mission requirements.
　For maneuvering the attitude of a micro-satellite, a compatible thruster system demands higher energy density (specific impulse) and higher precision (the resolution of impulse bit) as the size is miniaturized. As an acceptable performance, with its environmentally friendly characteristics, HTP is generally regarded as one of the “green propellants”. Having served on larger-scale propulsion systems with low cost, HTP is recently reconsidered to be a highly-desired candidate for the monopropellant micropropulsion system for use in micro-satellites. The main objective of this study is to develop a HTP microthruster system to meet the requirements of attitude control of a micro-satellite with mass bellow 50 kg, and the thrust in the range of hundred milli-Newtons.
　Specific problems and difficulties in design arise as the size of the HTP microthruster is reduced. The enhanced heat loss associated with size reducing immediately results in lower thruster operation temperature and poor decomposition efficiency. The two-phase phenomenon of gas bubble in liquid may also significantly affect the decomposition stability in the catalytic microchannel. Specific problems are investigated through theoretical and experimental studies and solutions are incorporated in the design modifications to overcome the problems, such as preheating and pH value adjusting.
　Theoretical analysis with isentropic assumptions is employed to determine the design and test parameters of the HTP microthruster. A prototype of the HTP microthruster packed with 0.7 g silver flake as catalyst is developed and tested. The overall thruster weighs 5.8 g. Test results show that more than 90% C* efficiency and 80% thermal efficiency are achieved with 91.5% HTP at the flow rate of 0.18 g/s. In the ground tests, the HTP microthruster generates 182 mN of thrust under atmospheric condition with a specific impulse bit 101 seconds and the system is expected to generate more than 170 seconds of specific impulse bit in vacuum.

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