基于遗传算法的液体火箭发动机参数优化
Optimization of liquid propellants rocket engine based on genetic algorithm
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摘要: 建立了液体火箭发动机系统设计的仿真模型和多目标优化模型,采用组合优化策略和遗传算法,针对全流量补燃循环发动机,进行了不同设计变量和目标函数下发动机性能参数的优化,求得全局最优解.计算结果表明,遗传算法是解决该类问题的有效方法,可为其它类似发动机的优化提供一定的指导作用.Abstract: The system simulation model and the relevant multi-objective optimization model were established for a type of liquid propellants rocket engine,by hybrid algorithm and genetic algorithm.Aiming at FFSC,performance parameters of engine were optimized under kinds of different design variables and objective functions,and got the global optimum solutions.The calculation results showed that genetic algorithm was the most available method to solve such a type of problem,also it could be guidance for other similar engine optimization.
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[1] 张黎辉,凌桂龙.氢氧全流量补燃循环发动机主要参数优化分析[J].航空动力学报,2006,21(5):937-942.ZHANG Lihui,LING Guilong.Optimal analysis of the main parameters of hydrogen-oxygen FFSC[J].Aviatic dynamic trasaction,2006,21,(5):937-942. [2] 莫斯卡连科ΓМ.火箭动力学中的工程设计方法[M].北京:宇航出版社,1984:68-73. [3] 竺苗龙.星际飞行中的几个问题[M].西安:陕西科学技术出版社,1980:112. [4] 中国航天工业总公司.世界导弹与航天发动机大全[M].北京:军事科学出版社,1999. [5] 朱宁昌,董锡鉴,王新龄,等.液体火箭发动机设计[M].北京:宇航出版社,1994:59-81.
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