Title: Effect of The Ratio of Fuel to Aft-Combustion Chamber Length on Thrust Characteristics of Hybrid Rocket Engine
Abstract: Hybrid rockets use different phases of oxidizer and fuel as the propellant to obtain thrust. Hybrid rockets have advantages such as higher safety, lower cost compared to conventional type rockets, and restart ability. However, they have the disadvantage of low thrust. The combustion chamber of a hybrid rocket engine requires the aft-combustion chamber for the fuel to complete chemical reaction before entering the nozzle. In other words, if the axial length of the aft-combustion chamber is insufficient, combustion will be incomplete and the combustion efficiency will be reduced. Therefore, the purpose of this study was to investigate the effect of the ratio of fuel to aft-combustion chamber length on the thrust characteristics of hybrid rocket engine and to optimize the length of fuel and aft-combustion chamber. The engine with a rated thrust of 10kgf was used in the experiment. Oxygen gas was used as the oxidizer and acrylic was used as the fuel. The fuel block lengths used in the experiments were 225, 150, 125, and 100mm. The effect of the ratio of fuel to aft-combustion chamber length on thrust characteristics was investigated.
Publication Year: 2022
Publication Date: 2022-01-01
Language: en
Type: article
Indexed In: ['crossref']
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