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題名 | 00mN等級過氧化氫微推進系統之研發=Development of a 100mN HTP Monopropellant Microthruster |
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作者 | 陳冠邦; 趙怡欽; 關智光; | 書刊名 | 致遠資工學刊 |
卷期 | 1:1 2007.04[民96.04] |
頁次 | 頁45-58 |
分類號 | 447.67 |
關鍵詞 | 高濃度過氧化氫; 微推進器; 銀觸媒; HTP; Microthruster; Silver; |
語文 | 中文(Chinese) |
中文摘要 | 本研究針對50kg級微型太空飛行器的姿態控制需求,使用自行純化之92%高濃度過氧化氫推進劑設計單推進劑微推進器,目標推力等級為 100mN。本研究藉由理論分析與初步測驗,獲得過氧化氫微推進器適合之操作參數,配合不同預熱條件下的測試得到相關性能特性。微推進器 原型內填充0.7g雪片狀銀觸媒,整體體積0.9㎤,質量5.8g。實驗結果顯示使用92%過氧化氫流量0.18g/s,其分解效率超過80%,分解溫度 最高可達約890K,觸媒床壓力5.86bar。地面測試量測推力為182mN,比衝值103s,據此推估真空中比衝值可達150s以上。 |
英文摘要 | A HTP (High test Peroxide) microthruster for maneuvering the attitude of small satellites is developed. The problems of miniaturization are investigated, the design concept of a 100mN HTP microthruster is proposed and the microthruster is demonstrated to perform a minimum impulse bit of 10[93be] N-s, which can provide a microsatellite slew at a speed of 0.1 degree per second. The total volume of the catalyst, and 92% hydrogen peroxide is adopted with a flow rate 0.18 g/s. Measurements of the ignition delay at different catalyst bed preheating temperatures are compared to define the operating parameters for practical applications. Test results showthat the HTP microthruster gives a fine C* efficiency and a short ignition delay comparable to the performance fo large scale systems. Under atmosphere pressure at seal-level, the developed microthruster can produce 182mN with a specific impulse 103 s. |
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