近年來混合式推進系統在太空發展上深受重視，而國內成功大學航太系成功的完成以N2O為氧化劑之混合火箭發動機及飛試元件研製。為因應太空系統的多元發展，本研究提出以N2O經由觸媒分解所產生的高溫燃氣做為混合火箭推進器點火系統的新穎構想，可有效簡化混合火箭點火系統，同時可以達到混合火箭重複點火的目的，進而發展一套多功能火箭系統。
研究中以過去發展30公斤推力級之N2O混合火箭為基礎，發展一套以同軸觸媒點火反應器與30公斤推力藥柱之整合式混合火箭發動機系統。本研究中將自N2O分解觸媒之研製、改良、分解測試開始，分析找出自主研製之觸媒的分解特性，並進而探討不同噴注器設計對於以觸媒分解氣體引燃混合火箭藥柱的點火延滯時間與點火操作特性的影響。
本研究利用自主發展的銥氧化物觸媒成功的使N2O有良好的分解反應，並透過分解反應測試找出預熱系統為60、70W下觸媒之負載能力，確認觸媒於推進系統上的適用性。另外，以此觸媒測試結果，在N2O流量為0.32g/s下利用其分解熱氣探討軸向噴注器在不同雷諾數與背向階梯擴張比例對於點火延遲時間之影響；並進一步設計渦旋噴注器以增進藥柱引燃，並進行測試，發現在雷諾數較小時搭配背向階梯效應所產生之迴流區，能使藥柱快速引燃。透過實驗測試找出最適當的重複點火機制。

The objective of this research is to develop a hybrid rocket igniter via using catalytically decomposed N2O to thermally ignite the fuel grain. The hybrid rocket program has been developed in National Cheng-Kung University for years. The hybrid rocket motor using liquid N2O as the oxidizer has been designed and demonstrated successfully. Accordingly, the novel ignition technology is necessitated to accomplish the feasibility of multi-function propulsion for spacecraft missions. In this research, manufacture, modification and demonstration of catalyst for N2O decomposition are addressed, and analyzing characteristics of N2O decomposition via laboratory-made catalysts is also conducted. Catalytically decomposed gas attempts to thermally ignite the hybrid rocket fuel grain, so that the configuration and layout of injection system are essential and pivot in ignition system. Consequently, corresponding effects of injector configuration on ignition delay and operational characteristics are further investigated in the study.
As to the laboratory-made catalyst, iridium oxide is impregnated onto metal meshes. The catalytic decomposition characteristics of nitrous oxide are performed via using 60-70W pre-heating system. Results confirm the feasibility of the laboratory-made catalyst applied in propulsion system. Therefore, according to the result of catalytic decomposition test, the N2O flow rate is fixed in 0.32g/s for ignition testing. The axial and swirl injectors are applied separately to discuss the effect of various Reynolds number and expansion ratio on the ignition delay time. The experimental results show the recirculation region induced by backward- facing step would apparently accelerate the ignition of fuel grain in low Reynolds number condition. Eventually, the proper multi-ignition mechanism of hybrid rocket is successfully verified and demonstrated by the series of experiments.

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