摘要
结合试验设计方法、替代模型技术和遗传算法构建一套改进的优化方法,并将其应用于高超声速飞行器后体/尾喷管的一体化设计.在构建优化方法时,针对替代模型采用渐近全局策略提高精度;针对遗传算法,采用实数编码、多目标定级排序和改进小生境技术.在后体/尾喷管的一体化设计应用中,结合高精度的计算流体力学(CFD,Computational Fluid Dynamics)求解,以两个设计点的推力和升力为目标,以力矩为约束,得到优化问题的Pareto最优前沿面,优化结果在综合性能方面有很大提升.该优化方法可进一步推广应用于更复杂的优化设计当中.
Through combining design of experiment（DOE）,surrogate models with genetic algorithms,modified optimization method was built,which was applied in the integrated design of afterbody/nozzle of a hypersonic vehicle.The sequential global surrogate models were developed to satisfy the computational demand.The issue of modifying genetic algorithms included the real number coding,niche technique and multi-objective classrank skill.In the optimization question,precise computational fluid dynamics（CFD） were used,thrust and lift were used as the performance objects,moment were used as constrain,and the Pareto front was gotten.After the optimization,the thrust and lift force of the nozzle has a great improvement.As a method,this algorithm can be applied in the optimization design with a more complex flow model.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2011年第11期1440-1445,共6页
Journal of Beijing University of Aeronautics and Astronautics
基金
基础研究发展计划资助项目(2009CB724104)
国家自然科学基金资助项目(90716010)
关键词
高超声速飞行器
后体/尾喷管
优化设计
遗传算法
替代模型
计算流体力学
hypersonic vehicle
afterbody/nozzle
optimal design
genetic algorithms
surrogate models
computational fluid dynamics（CFD）
