Experimental study on burning rate of sub-scale H₂O₂/HTPB hybrid rocket motor grain

The experimental researches on solid fuel regression rate of sub-scale hybrid rocket motor with the hydrogen peroxide (H₂O₂) and hydroxyl-terminated polybutadiene(HTPB)-based propellant combination are presented in this paper, and the solid fuel regression rate data under various ignition modes and oxidizer mass flux are carried out. The results show that with catalytic bed ignition mode, the fuel regression rate is higher and the chamber pressure is more stable, but longer chamber pressure build-up time is needed. According to the calculated experimental fuel regression rate of various oxidizer mass flux, a fuel regression rate formula is fitted when the motor is ignited with solid fuel. The solid fuel grain design of φ300 mm full-scale rocket motor and interior ballistics performances calculation are produced based on the fitted fuel regression rate formula, and the theoretic curves fit well with the experiment results, which validate the method and results of fuel regression research in this paper.