Design and integrated simulation of a pressurized feed system of the dual-thrust hybrid rocket motor

A new pressurized feed system of the dual-thrust hybrid rocket motor for flight is presented in this paper. The feed system supplies 90% hydrogen peroxide (90%H₂O₂) with two different flows of 4.5 and 2 kg s^-1. The oxidizer flow is changed through regulating the mass flow of the high-pressure gas and switching the performance modes of the unique oxidizer flow control valve simultaneously. The models of the gas storage container, pressure regulator valve, control orifice, propellant tank, oxidizer flow control valve and cavitating venturi are generated and used to compute the instantaneous pressure, temperature and mass flow rate. There is a good agreement between the simulated and experimental results. Parameter sensitivity analysis is also conducted. It is found that the throat diameter of the cavitating venturi in feed line 1 is the main factor affecting the mass flow in both boost and sustaining phase. Other parameters have limited effects on the mass flow rate and the transition time of the system.