混合火箭系統因具備高安全性能與低成本優勢，近年來無論是各國研究單位乃至民間太空科技業者均紛紛投入相關研究領域，然而混合火箭發展至今受到推進性能限制，現階段多用於任務型態簡易之探空火箭實驗，為提升混合火箭實際投入複雜太空任務的可行性，本研究主力發展混合火箭自發點火關鍵技術，實現在不裝配外部點火系統即能夠自發點火的混合火箭發動機構想。
本研究將燃料添加物混摻黏著劑製成燃料藥柱，使高濃度過氧化氫與觸媒藥柱直接接觸，於接觸面上之異相化學反應伴隨釋熱發生，造成周圍燃料以及氧化劑汽化並點燃，發動機自發點火的關鍵機制在於觸媒反應面上之液滴汽化與觸媒分解，過氧化氫之自分解反應伴隨液滴汽化發生，未反應完全之氧化劑於燃料藥柱表面溢流將造成發動機無法成功點燃，由於自發點火式混合火箭至今為止並非發展主流，因此相關設計參考資料並不普遍，本研究藉實驗觀察氧化劑液滴與觸媒燃料之反應情形，初步篩選能夠點燃之燃料與添加物配方並製成燃料藥柱，更進一步整合氧化劑噴嘴組成發動機，完成自發點火混合式火箭之原型測試，並透過改變氧化劑噴助條件以及搭配可視化之發動機實驗觀察，探討氧化劑溢流現象對於點燃延遲之影響，本研究初步瞭解發動機之接觸點燃機制，實驗所蒐集到之退縮率資料亦能作為後續發展大型自發點火式混合火箭之參考。

With the inherent merits of high maneuverability, hypergolic rocket system is extensively utilized in difficult and complicate space missions, such as planetary landing and orbital injection. Hybrid rockets with hypergolic feature is capable of producing reliable rapid ignition and generating thrust without additional ignition device. Hypergolic mechanisms utilized in hybrid rockets also have enormous research potential which can develop into throttling and restartable propulsion system and fulfilling the functionality of hybrid rocket propulsion. In this research, hypergolic features are achieved by the use of high concentration hydrogen peroxide as oxidizer and catalyst-added fuel grains, a mixture of plastic binder and catalyst for the decomposition of hydrogen peroxide. It is found that as hydrogen peroxide droplets contact with catalytic propellant surface, the exothermic heterogeneous reaction is initiated on the interface and heats up fuel grain surface inducing motor ignition. By modifying the oxidizer operating conditions and fuel grain configurations, we have shown reliably successful ignitions of the motor within a short period of time (<0.5sec) in hot fire experiments, and based on the trend of pressure rise the hypergolic starting characteristics can be classified into three different kinds of ignition processes. From the experimental observation using the transparent motor, we infer that the motor starting characteristic is related to the interaction of hydrogen peroxide droplets and catalytic propellant surface inducing flooding and splattering phenomena when liquid oxidizers impact on propellant surface, that may lead to hard-start or smooth-start of the rocket motor.

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