於雙基液態火箭推進劑中，若使用具備自燃特性之推進劑，則不需使用點火裝置，可降低火箭系統中的複雜性與重量。於本研究中，以自行研發出具高熱值、無毒且高儲存性的燃料W2為基礎，並改變觸媒調配方式，調配出一系列新型配方，於液滴接觸實驗中，對各燃料配方之點火特性進行探討。其中配方W3與過氧化氫之自燃點火延遲約為20 ms，比衝值高於310秒，並具有良好保存特性。
本研究也以W3與過氧化氫搭配自行設計之液旋式噴注單元(內徑14mm，長度21mm)進行熱燃實驗，於每秒流量15.75克至49.5克之間，皆可在200ms內成功自燃點火。根據觀察，於流量高於每秒22.5克的條件下屬於外部點火，此時點火延遲及火焰分布較易受環境影響；當流量低於22.5克時會於噴注器內部穩定點火並形成緊實的火焰，此操作條件，可供後續500磅級液態火箭噴注盤設計參考。

For bipropellant rocket engines, the complexity and weight of a rocket engine can be reduced if the hypergolic propellant system could be operated without an ignition device. In recent years, the NCKU Liquid Rocket Propulsion Lab has developed W2 fuel which has high heating value, non-toxic, and high storage properties. However, due to the low concentration of soluble catalyst, the ignition delay time is relatively long. Therefore, a series of new fuel formulations were developed to keep the advantages of W2 and to further reduce the ignition delay time. In this study, droplet tests were firstly adopted to observe the ignition characteristics of different proportions of fuel formulations. At the same time, experiments and calculations were designed to explore the storability, specific impulse, and adiabatic flame temperature. Lastly, the liquid cyclonic injector was also improved. The modified liquid cyclonic injector was used with the pressure swirling injector for a hot-fire experiment with the new formulation, to find out the data on chamber design.

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