| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系 === 104 === Hypergolic effect of propellants is an important characteristic for rocket propulsion. Traditional hypergolic propellant system, such as MMH/NTO, is toxic and corrosive. This research chooses 95% Hydrogen peroxide (H2O2) and W2 to be the research subject for their low toxicity and corrosion. W2 is a Kerosene base fuel mixed with manganese acetate, which has high heating value and Isp when works with H2O2 in rocket propulsion. However, its catalyst content is limited so as to have a relatively long auto-ignition delay time in contact with hydrogen peroxide. Flat plates of silver (Ag), platinum (Pt) and manganese dioxide (MnO2), work as heterogeneous catalysts are adopted in this research to analyse the improvement of the auto-ignition of H2O2/W2 system. By varying the total liquid flow rate, O/F ratio, and heterogeneous catalyst, the ignition delay times are compared and analyzed. The experimental observation shows the ignition process can be divided into three stages: liquid mixing, liquid phase heat releasing reaction, and gas phase ignition reaction. The result shows when the total mass flow rate is increased, the ignition delay time decreases that may cause by the better mixing of the two liquid, and, heterogeneous catalyst of MnO2 do effectively improve the auto-ignition of H2O2/W2 system, however, Ag and Pt do not. The experiments also show the powder-like manganese oxides from reactions depositing on the solid surface strongly activates the decomposition of hydrogen peroxide.
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