Design Parameter Optimization of Liquid Rocket Engine Using Genetic Algorithms

초록

Design variables of liquid rocket engine have been optimized using a genetic algorithm. Pressure of the main combustion chamber, nozzle expansion ratio and O/F ratio have been selected as design variables. Gas generator cycle using the LO2/RP-1 had been chosen as the target engine. The gas properties of the combustion chamber were obtained from CEA2 and mass of the engine was estimated using reference data. The objective function was constructed as multiobjective function with the specific impulse and thrust to weight ratio using the weight method. The result shows about 4% improvement of the specific impulse and 23% increase of the thrust to weight ratio. The Pareto frontier lines were also obtained for various thrust requirements.