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建立了固液混合火箭发动机的仿真模型和相应的单目标和多目标优化模型,编制了系统仿真程序;采用差分进化算法针对不同的优化目标对发动机的参数进行优化;针对挤压式系统建立了质量模型,在优化过程中考虑了主要部件结构质量对发动机性能的影响;针对固液发动机常用的侧面燃烧药柱编制了内弹道计算程序。以药柱几何参数、氧化剂流量、燃烧室平均工作压强和喷管扩张比等参数为设计变量,对发动机平均比冲、总质量、关机时飞行速度和密度比冲等性能参数进行优化,在Pareto分析的基础上选择了氧化剂流量、燃烧室平均工作压强和喷管扩张比对发动机性能的影响作了深入研究;最后对某型固液发动机进行了优化分析。
The simulation model of solid-liquid hybrid rocket motor and corresponding single-objective and multi-objective optimization models are established, and the system simulation program is compiled. The differential evolution algorithm is used to optimize the parameters of the engine for different optimization objectives. For the extrusion system, Quality model, the influence of the quality of the main components on the performance of the engine was considered in the optimization process; and the internal ballistics calculation program was compiled for the side-fired combustible particles commonly used in solid-liquid engines. The performance parameters such as average specific impulse of the engine, total mass, specific velocity of the flight at the time of shut-down, density and density were optimized by taking parameters such as the geometric parameters of the grain, the flow of oxidant, the average working pressure of the combustion chamber and the expansion ratio of the nozzle as the design variables. Based on the analysis, the effects of oxidant flow rate, average working pressure of the combustion chamber and nozzle expansion ratio on the performance of the engine are deeply studied. Finally, a solid-liquid engine is optimized and analyzed.