무게를 고려한 액체로켓엔진의 설계변수 최적화

초록

Design variables are decided by parametric system analysis in preliminary design of the liquid rocket engine. In this paper, the liquid rocket engine's design variables are optimized by mass estimation and system analysis which consists of the thrust chamber, turbo-pumps, the turbine and the gas-generator. Design variables are set up by main chamber pressure, nozzle expansion ratio, and O/F ratio. Also the objective function is defined with both specific impulse and thrust/weight ratio. A measure of the function concerning nozzle expansion ratio, thrust and main chamber pressure is taken for the mass estimation. In conclusion, it is ascertained that the relationship of the optimized specific impulse and the maximum of thrust/weight ratio is qualitatively reasonable.