Design specifications of H2O2/kerosene bipropellant rocket system for space missions

Abstract Over the last decade, interest has been rekindled on hydrogen peroxide as a rocket propellant. As a result, 1000-N-class H 2 O 2 /hydrocarbon bipropellant rocket systems are in a stage requiring a serious exploration for application. Application to orbit-raising maneuvers is proposed here as the most appropriate use of the 1000-N-class thrusters. In this study, optimal design specifications of a 90% H 2 O 2 /kerosene rocket system for an apogee kick motor were derived. The optimal design specifications are configured with a thrust of 742 N, a chamber pressure of 11.7 bar, a mixture ratio of 7.36, and a nozzle expansion ratio of 580. It was found that, in the case of the latest Korean geosynchronous satellite, replacing the current apogee kick motor with the H 2 O 2 /kerosene rocket system would result in a mass increase of less than 0.5% of the total mass.