Dynamic modeling of a specific electro-pump liquid-propellant rocket

This research aims to model the nonlinear dynamics of the space propulsion system equipped with an electro-pump. For modeling, this system includes the combustion chamber, fuel and oxidizer tanks, and the corresponding pressurization system. A set of governing equations has been modeled in the Simulink of MATLAB software. The results of the modeling including changes in the angular velocity versus the time, changes in combustion chamber pressure versus the time, and changes in the mass flow rate of the fuel and oxidizer to the combustion chamber versus the time, are presented. In the end, the obtained results are compared with the results of the available engine and in addition to validating the results, it is possible to confirm and validate the performance of the electro-pump in a liquid fuel engine. The results showed that the angular velocity rate, the average acceleration rate of the combustion chamber, the average flow rate of the oxidizer to the combustion chamber and the average flow rate of the fuel to the combustion chamber obtained from the simulation and the available reference have a maximum error of 20%. The amount of difference in the conceptual design stage is free of problems. In addition, the trend of the graphs is similar.