局所燃料後退速度に基づく酸化剤流旋回型ハイブリッドロケットエンジン性能パラメータの時刻変化予測手法について

概要

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Our experimental studies showed that there were two different combustion regions in the combustion chamber of the swirling-oxidizer-flow-type hybrid rocket engine. The front region near the injector had higher values of the local fuel regression rate than those in the rear region, and the rates in the rear region were almost the same along the length direction. We established the combustion model to predict the engine performance with swirling oxidizer flow, in which the combustion chamber region was divided into the front and rear regions. In the front region, the local fuel regression rates were given as time constant values independent of the grain port area. In the rear region, the regression rates were given by a new formula which included the effect of the swirling oxidizer flow. It was found that the simulation results were well in agreement with the experimental results about the time variations and values of the chamber pressure and thrust. The issues in application of this new prediction method to the other swirling-flow-type engines using a different fuel and an injector were discussed.