Small Rocket Launch Experiment using Low Melting Point Thermoplastic Fuel/N_2O Hybrid Rocket

摘要

Hybrid rocket using Low Melting Temperature Thermoplastics (LT) fuel as a solid fuel has been studied. The LT fuel has higher regression rate than classical inert polymer fuel such as a Hydroxyl-Terminated-PolyButadiene (HTPB), and an excellent mechanical property as same as solid propellants. Efforts has been paid successfully to enhance the adhesion property against metallic casing and linear material, and thus, the fuel looks promising for the application to large scale motors. As the first step, small hybrid rocket was launched by LT/N_2O hybrid combination on the basis of the experimental data of regression rate using a lab. scale hybrid rocket motor. In this paper, the detailed discussion of this successful launch is presented.