Design optimization of liquid rocket engine using a genetic algorithm

In the preliminary- design of the liquid rocket engine, design parameters are determined by system analysis considering requirements and constraints. In this study, the design optimization program using a genetic algorithm has been developed to obtain design parameters for the best performance. The program consists of a system analysis section and an optimization section. The system analysis section is composed of subsystem analysis program modules such as the thrust chamber module, the gas-generator module, the turbo pump and turbine module. Each subsystem module provides performance parameters and weight for the LRE(I.iquid Rocket Engine) system module which calculates the specific impulse and the thrust to weight ratio. In order to maximize these values, the multi-objective function has been established using the weighted sum method. As a result, the Pareto frontier lines have been obtained for various thrusts. The results compared to performance data of real engines show that the program is suitable for the design optimization. The program is expected to improve efficiency and performance of liquid rocket engines in the preliminary design proccss for the space launch vehicle design.