00mN等級過氧化氫微推進系統之研發

Development of a 100mN HTP Monopropellant Microthruster

陳冠邦(Guan-Bang Chen) ； 趙怡欽(Yei-Chin Chao) ； 關智光(Chin-Kunag Kuan)

《資訊工程學報》 1卷1期 (2007/04) Pp. 45-58

https://doi.org/10.6600/BCIE.2007.1(1).4

摘要

本研究針對50 kg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100 mN。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0.7 g雪片狀銀觸媒，整體體積0.9 cm^3，質量5.8 g。實驗結果顯示使用92%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。地面測試量測推力為182 mN，比衝值103 s，據此推估真空中比衝值可達150 s以上。

關鍵字

高濃度過氧化氫 ； 微推進器 ； 銀觸媒

並列摘要

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 100 mN HTP microthruster is proposed and the microthruster is demonstrated to perform a minimum impulse bit of 10^(-2) N-s, which can provide a microsatellite slew at a speed of 0.1 degree per second. The total volume of the microthruster prototype is about 0.9 cm^3 with a throat diameter 0.5 mm packing with silver flake as 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 show that the HTP microthruster gives a fine C* efficiency and a short ignition delay comparable to the performance of large scale systems. Under atmosphere pressure at sea-level, the developed microthruster can produce 182mN with a specific impulse 103 s.

並列關鍵字

HTP ； microthruster ； silver