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.
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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第5期916-920,共5页
Journal of Aerospace Power
关键词
航空、航天推进系统
液体火箭发动机
系统分析
弹道
优化
遗传算法
aerospace propulsion system propellant rocket engine
systems anal ysis
trajectory
optimization
genetic algorithm
