摘要：A new pressurized feed system of the dual-thrust hybrid rocket motor for flight is presented in this *** feed system supplies 90% hydrogen peroxide (90%H 2 O 2) with two different flows of 4.5 and 2 kg s *** 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 *** 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 *** is a good agreement between the simulated and experimental *** sensitivity analysis is also *** 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 *** parameters have limited effects on the mass flow rate and the transition time of the system.