過氧化氫預分解混合火箭具備高空點火、重複點火、推力調控功能，且安全性高，被視為發展上層火箭的潛力技術。本實驗室過去成功建立30kgf 過氧化氫預分解混合火箭及相關參數資料，然而在測試過程中發現旋流噴注器因燃燒室熱回朔而燒蝕的現象，在後續研究中，利用中心液態過氧化氫噴注吸收燃燒室多餘熱能來保護旋流噴注器，並順利將推力提升至300kgf，但於後續點火測試發生爆炸。
透過影格、實驗證據、文獻資料分析，判斷爆炸起因於過氧化氫分解不佳，而旋流噴注器燒蝕則因其下游中心回流區高溫所致。故本研究改善噴注器流道設計賦予其初步限制開閥流量並均勻散佈過氧化氫之功能，在良好的噴注器設計下適度減少觸媒用量以減低觸媒床壓降，同時增加擋板強度來穩固觸媒床整體結構，預期透過上述改良使發動機在點火建壓前的暫態階段不會落入大量過氧化氫分解不完全的情況；熱回朔問題則改良旋流噴注器構型使過氧化氫分解氣流通過其中央，以此破壞或將中心回流區往更下游移動，避免與旋流噴注器直接接觸，防止燒蝕。
透過實驗證實本研究開發之過氧化氫噴注器流量限制效果明顯，預分解段可將過氧化氫快速分解至氣相反應期間並順利點燃發動機，觸媒床反應趨於穩定，且反應時間接近發動機點火延遲時間，實驗過後擋板亦無變形，觸媒床整體結構穩固，與300kgf系統比較，本系統之觸媒床壽命提升至少三倍，仍可進行後續測試；本研究亦於5秒的發動機點火測試證實將中心回流區往下游移動的方法可有效抑制熱回朔，以更簡易的機構設計保護旋流噴注器。
本研究奠基於實驗室過去開發之經驗、數據、觸媒及發動機基礎構型，透過解決爆炸及燒蝕問題成功開發200公斤級推力過氧化氫預分解混合火箭。

One of advantages of pre-decomposition hydrogen peroxide (HP) hybrid rocket is the possibility of initiating its catalytic decomposition without using an additional igniting device. This simplifies the design of the motor and makes it has great potential to be upper stage rockets. The decomposition rate of HP is one of the most important parameters in the development of pre-decomposition hydrogen peroxide hybrid rocket. The injector developed in this study can constrain the overshoot in transient of the HP mass flow rate which is about twice of the steady flow rate and distribute it evenly. With the proper injector design, the catalyst filling amount that leads to pressure drop in the catalyst pack is reduced and the catalyst bed meets the requirement of complete decomposition of concentrated HP right after the valve opening. By experimental results, it was found that the time of reaching the steady-state is about 0.44s and is very close to the 50P fuel grain engine ignition delay time. Compared with the 300kgf system invented in our laboratory in the past, the operation life of the catalyst bed in this study is increased by at least three times and is still able to work normally. This study also verifies that the effect of HP decomposition gases flow can push the central recirculation zone to downstream of the swirler which can prevent the heat from the combustion chamber that causes thermal ablation. Finally, a motor of 200kgf Pre-decomposition HP Hybrid Rocket is successfully developed and demonstrated.

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