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建立了某液体火箭发动机系统设计的仿真模型与相应的多目标优化模型,编制了系统仿真程序,并在iSIGHT的软件平台上针对不同的优化目标对发动机的设计参数进行优化.采用了组合优化策略,结合多岛遗传算法和序列二次规划算法分别进行全局寻优和局部寻优,求得全局最优点.建立了单燃气发生器循环系统的质量模型,在优化过程中考虑了发动机主要部件结构质量对系统性能的影响。以燃烧室压强、混合比和喷管出口反压为设计变量,优化目标包括发动机比冲、有效载荷、结构质量、密度比冲、关机时飞行速度、推进剂综合密度.并根据结果分析了燃烧室压强和混合比对发动机性能的影响.
The simulation model and the corresponding multi-objective optimization model of a liquid rocket engine system are established, and the system simulation program is compiled, and the design parameters of the engine are optimized for different optimization objectives on the iSIGHT software platform.Optimization strategy , Combined with multi-island genetic algorithm and sequence quadratic programming algorithm, respectively, for global optimization and local optimization, to find the global optimum.The mass model of the single gas generator circulation system was established, and the main components of the engine were considered in the optimization process The impact of quality on system performance. The optimization objectives include engine specific impulse, payload, structural mass, density ratio impulse, flight speed at shut-down, integrated propellant density, based on the results of combustion pressure, mixing ratio and nozzle outlet backpressure as design variables Effect of chamber pressure and mixing ratio on engine performance.