关键词: 固液混合火箭发动机;系统仿真;内弹道;质量模型;装药设计;多目标优化

Abstract: The simulation model and the relevant multi-objective optimization model were established for hybrid rocket motor.A system simulation procedure was programmed.Design parameters of the system were optimized owing to different optimization objectives based on differential evolution algorithm.Weight model of gasbag pressurized system was established.Main components weights were concerned in optimization because of their influence on system performance.An interior ballistics procedure was programmed for side burning grain applied in hybrid rocket motor.The optimization design variables were geometrical parameters of grain,oxidizer flux,combustor averaged pressure and expansion ratio of nozzle.The optimization objectives were averaged specific impulse,weight,density specific impulse and flight speed at shutting down.The effects of oxidizer flux,combustion chamber averaged pressure and expansion ratio on motor performance were analyzed based on DOE and pareto analysis.At last,a hybrid rocket motor was optimized and analyzed.

Key words: Hybrid rocket motor;System simulation;Interior ballistics;Weight model;Grain design;Multi-object optimization