Simulation and optimization of liquid propellants rocket engine for system design

The system simulation model and the relevant multi-objective optimization model were established for a type of liquid propellants rocket engine. A system simulation procedure was programmed. Design parameters of system were optimized owing to different optimization objectives on iSIGHT software platform. A type of hybrid algorithm, which combined the multi-island genetic algorithm and the sequential quadratic programming algorithm, was used to find global optimum in given design space during the optimization procedure. Weight model of single gas generator cycle system was established. Main components weights were concerned in optimization because of their influence on system performance. The optimization design variables were the combustor pressure, mixture ratio, and the outlet pressure of pipe. The optimization objectives were engine specific impulse, payload, engine weight, engine density specific impulse, flight speed at shutting down and engine compositive density. The effects of combustion chamber pressure and mixture ratio on engine performance were analyzed based on simulation.