定格推力５０ｋｇｆ級小型ハイブリッドロケットエンジンの燃焼実験

抄録

The purpose of this research is to develop a rated thrust 50kgf class small hybrid rocket engine. In the previous experiment, the injector was damaged due to abnormal combustion in the engine. The cause is that the ignitor was blocked inside the fuel port because the ignitor was larger than the fuel port and nozzle throat diameter. In this study, we investigated the effect of smaller ignitor and a baffle plate installed in the downstream side of the fuel. As a result, the following conclusions. (1) Abnormal combustion didn’t occur. (2) By installing the baffle plate, residential time of paraffin wax becomes longer and promote combustion. (3) The rated thrust reached 50kgf even when the ignitor was smaller. However, in this experiment, the thrust decreased from the middle of combustion time. Combustion is promoted by casting a paraffin wax having a melting point lower than that of acrylic resin. However, since the combustion of paraffin wax ended in the middle of combustion and switched to the combustion of acrylic resin only, the regression rate was reduced and the thrust was thought to have decreased.