Design, Manufacture and Experimental Study of a Hydrogen Peroxide-HTPB Hybrid Rocket Motor

he application of the hydrogen peroxide as the oxidizer of a HTPB-based prototype ybrid motor is investigated in this paper. First of all, by studying the thermochemical haracteristics of the propellant,operation range of different compositions is defined. A rototype hybrid motor is then designed and manufactured, which is able to produce 10 kg propellant thrust. Conducting a special procedure available stabilized commercial hydrogen peroxide is processed and converted to a 90% density propellant which has less than 15 ppm tainting. A catalytic igniter is used in order to fire the motor. It was observed that the approach of employing the oxidizer to the catalyst bed is highly effective on the quality of the system performance. So, the injection quality of the oxidizer was investigated for different mass flow rates. The performance of the hybrid motor by HTTPB fuel is studied in a successful experimental test. The results of the test including the pressure and characteristic velocity are compared with the predicted theoretical simulations. Moreover, the performance specifications of the motor like the regression rate are determined and compared with the similar researches.