Abstract:

Abstract A liquid rocket engine has an open gas generator cycle that uses LOX/RP-1 (kerosene). The engine is designed to com-pute the size of the combustion chamber pressure, nozzle expansion ratio, and mixture ratio O/F. Therefore, this study proposes particle swarm optimization to determine the values of these three variables for an optimal engine. In this work, the engine’s design was obtained through multi-objective optimization. Multiple targets presented the energy balance condition. The first function was the setting of the specific impulse (I_sp), and the second function was the thrust-to-weight ratio (T/W). The physical properties of the combustion chamber were modeled on the basis of typical parameter val-ues. The simulation results demonstrated that the algorithm gave a specific thrust increase of more than 3.5%, and the T/W increased by up to 20%. Furthermore, Pareto frontier lines were obtained for various thrust.

Keywords: