在火箭推進的領域中，混合火箭佔有重要的一席之地，不過其相關研究大多著重在退縮率經驗公式的推導、增加退縮率、或是放大效應等主題上，對於點火後之火焰傳遞以及火焰穩駐的基礎現象研究則較少著墨。本篇論文則是利用一自行設計之可視燃燒器來探討混合火箭火焰由點火、傳播到穩駐的這段混合火箭點火過程。
首先利用了邊界層理論計算出了可能的火焰高度隨位置之變化，同時也利用CFD數值模擬未點火之流場的濃度分佈，並將上述兩者與實驗照片加以比較，證明混合火箭之火燄位置會位在偏富油端，而濃度場分佈主要為紊流邊界層主導其擴散與混合。
在確立點火方式後對此觸媒網點火系統進行特性探討，此系統主要是藉由建立一初始火焰來作為一熱源提供者，穩定的預熱藥柱與氧化劑，於點火4~6秒後建立一自我維持的火焰。而文章中也對此觸媒網系統與混合火箭之點火、傳播、與穩駐進行了時間與能量的詳細分析。另一方面則是找出於目前系統下之吹熄流速(8.02m/s)，並利用一5mm之背向階梯流場成功將可操作區間流速提升至11.88m/s，於此同時也檢視階梯對燃燒行為的影響(包含預熱效果、燃燒效率等等)。最後則是在有階梯的流場情形下，進行了CH*自然螢光燃燒場診測，更進一步的證明上述對於氧化亞氮/HTPB-石蠟混合火箭火焰點火與穩駐機構之論述。

Hybrid rocket played an important role in many research of propulsion. Most of them related to the derivation of regression rate、increasing the regression rate、and the scale-up effect. The mechanism of flame propagation and stabilization didn't attract much attention in these literature. In this study, a visible combustor was designed to investigate flame ignition and stabilization mechanism of a nitrous oxide /HTPB-paraffin hybrid rocket.
The flame position versus various free stream velocity were predicted by the boundary layer theory. The distribution of species concentration were computed by CFD(cold flow results). These results were compared with experiments. It indicated the flame lay on the fuel rich side rather than the stoichiometric line, and the distribution of species concentration were dominated by turbulent boundary layer.
In the experiments, the characteristic of the catalytic web igniting system were examined. The catalytic web established a primitive flame to preheat the solid fuel and the oxidizer at first. Then a self sustained flame will establish within six second after the ignition. The time trace and energy analysis for the interaction between igniting system and hybrid rocket were explained. The blow-off limit for this system was found((8.02m/s). The operational range of velocity were increased by the additive of the backward-facing step. The system could have a steady combustion at 11.88m/s by a step height of 5mm. Finally, the measurement of the CH* radical proved the above statements of the flame ignition and stabilization mechanism of a nitrous oxide /HTPB-paraffin hybrid rocket again.

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