Autoignitable and Restartable Hybrid Rockets Using Catalytic Decomposition of an Oxidizer

摘要

The autoignition characteristics of hybrid rockets were studied using hydrogen peroxide as an oxidizer. A catalytic reactor to decompose the oxidizer was designed, and the characteristics of ignition of the improved hybrid rocket, which combined a reactor and a combustor, were presented. Characteristics such as 1) autoignition, 2) restartability, and 3) immediate ignition using paraffin and polyethylene (PE) as the fuel of the hybrid rocket were compared. The values of specific impulse, characteristic velocity, and adia-batic flame temperature for both fuels are nearly identical. A different hybrid rocket design is needed, because of burning behavior. In identical oxidizer flow conditions, a hybrid rocket that used paraffin had a longer characteristic length of combustor than PE, due to the lack of mixing efficiency. In terms of ignition, paraffin was better than PE. Paraffin, having a low melting point and low ignition temperature, ignited in the first pulses and had a faster response time than those of the monopropellant or of PE. Positive possibilities were shown in terms of the attitude and position control for propulsion systems.