Numerical Analysis On Dynamic Characteristics Of Liquid Rocket Propulsion System

According to the methodology of modularization modeling and simulation, the simulation module components of the liquid rocket propulsion system are constructed based on AMESim software. Then the general model of rocket engine system is set up by connecting the corresponding simulation components and the transient processes of different kinds of engine system are simulated.The liquid propellants propulsion system is divided into the supply pipeline, tank pressurization system, turbopump system, thrust chamber, valves and auto components, etc.. Correspondingly, the mathematical models are established as the basic modules of the system such as liquid pipelines, gas pipelines, tank, centrifugal pump, turbine, rotors, injectors, combustion chamber and nozzle, the cooling jacket, valves and regulators and so on.Using the model libraries and development tool provided by AMESim software, the basic components' simulation models of the propulsion system are developed. The relief valve, gas generator, turbopump and other components are tested to demonstrate the accuracy and effectiveness of the simulation models.On the liquid oxygen tank pressurization system design, a gas-pressurized system with gas cylinders and vaporized self-pressurization system are simulated. The simulation results are scheduled to meet the pressure and flow requirements. Comparing the pressurization efficiency among the helium, nitrogen and air, the results show that helium is the most efficient pressurized gas.An attitude control and orbit control engine system is designed to be used on rockets and satellites. Based on AMESim software, the subsystems and whole system testing platforms are built and the entire working process is simulated. The results show that the simulation model can be better able to perform the actual work features of the engine system and simulate the engine start-up, shutdown, the impulse response, water hammer and other phenomenon during the operating time.For hydrogen peroxide/kerosene variable thrust engine system, the relationship between the flow resistance and the mass flow rate of the catalyst bed is studied. The head filling injection components and catalytic bed components are developed with AMESet. The simulation model of the whole engine system is established and the working course simulation is carried out, we can be informed of the dynamic characteristic during the process of thrust regulating.