近年來，由於環保意識的提升以及降低研發成本的考量，像過氧化氫這類無毒性但又具有強氧化力的推進劑漸受重視，以取代如聯胺等的強毒性火箭推進劑。由於過氧化氫具有很高的分解熱，使得分解後的氣體溫度可以非常高，甚至可達1000℃左右，因此，非常適合用在單推進劑液態火箭上。此外，過氧化氫也可以與煤油、火箭燃油（RP-Fuel）等燃料形成雙推進劑液態火箭，其性能甚至不輸給MMH與NTO的組合。
　　本研究之目的為設計並測試一具以過氧化氫以及汽油為雙推進劑的液態火箭，所使用的催化劑為過錳酸鉀，點火方式採用能量較高的火藥點火方式。此火箭屬於二階段反應之雙推進劑液態火箭，第一階段為過氧化氫與過錳酸鉀反應，分解產生高溫的氧氣與水，第二階段則是汽油與氧氣的燃燒反應。本研究曾針對不同比例的火藥組成做測試，並觀察其燃燒現象，紀錄火焰溫度與燃燒時間，建立了相關的資料庫。
　　經由50%過氧化氫分解測試中可發現，即使過氧化氫流量高達9.7 kg/min，催化後的溫度依然可維持在130℃左右，分解效率可達80%以上，顯示過錳酸鉀有足夠的時間與過氧化氫反應。
火箭整合測試結果顯示，目前已經能夠成功點火並持續燃燒，燃燒室也已經可以建壓至240 psia以上，推力也可達56 lbf以上，而比衝值則在60~100秒之間。

　　Recently, because of the rise in environmental consciousness and under the consideration of cost reduction, toxic propellants such as MMH has gradually been replaced by non-toxic and powerful propellants such as hydrogen peroxide. Due to the high decomposition heat of hydrogen peroxide, the decomposed gases come with very high temperature, so it is very suitable for using in both mono-propellant and bi-propellant liquid rockets.
　　The purpose of this study is to design and test a hydrogen peroxide(50%) / gasoline bi-propellants liquid rocket with catalyst potassium permanganate. The ignition is carried out by powder compound. This rocket is designed in a two-stage of reaction; In the first stage, hydrogen peroxide reacts with potassium permanganate to produce high temperature oxygen and water vapor, and these high temperature gas further reacts and burns with gasoline in the second stage.
　　It is shown that decomposition temperature is not influenced by peroxide flow rate. The decomposition temperature is about 130℃, and the decomposition efficiency is higher than 80% all the time. It reveals that the peroxide has enough time to react with catalyst.
In the hot firing test, it is shown that successful ignition and combustion can be maintained continuously, and the maximum chamber pressure is measured about 240 psia, maximum thrust is around 56 lbf, and its specific impulse is about 80s±20s.

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