Studies on the Design of Hydrogen Peroxide / Gasoline Liquid Rocket

• Main Authors: Ching-Sung Chen, 陳菁菘
• Other Authors: Wei-Hsiang Lai
• Format: Others
• Language: zh-TW
• Published: 2004
• Online Access: http://ndltd.ncl.edu.tw/handle/20138130665926583449

碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 92 === 　　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environmental consciousness and under the consideration of cost reduction, toxic propellants such as MMH has gradually been replaced by non-toxic and powerful propellants such as hydrogen peroxide.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.