超燃冲压发动机二维进气道的遗传优化设计方法  

Optimization Design of Two-dimensional Scramjet Inlet Based on Genetic Algorithm

作　　者：李舰[1] 沈娟[2] 

机构地区：[1]北京航空航天大学,北京100081 [2]北京海鹰科技情报研究所,北京100074

出　　处：《战术导弹技术》2008年第5期30-32,48,共4页Tactical Missile Technology

摘　　要：基于一维分析方法和计算流体力学方法,提出了一种可以自适应搜索的遗传优化方法.选择总压恢复系数作为目标函数,进气道的增压比作为约束条件,对四楔角混合式二维进气道进行了优化设计.结果表明,该方法能够有效地降低计算成本,可以提升超燃冲压发动机进气道的设计水平,得到高性能的设计方案.A self-adaptive optimization design method is presented and applied to the problem of mixed inlet of two-dimensional scramjet with four compression ramps based on genetic algorithm. One-dimensional solver and computational fluid dynamics （CFD） solver are linked within an automated loop. Total pressure recovery coefficient is selected as performance objective function with the restriction of static pressure rise. The results of optimization show that the serf-adaptive method can save computational expense and improve high performance scramjet inlet design.

关 键 词：超燃冲压发动机 高超声速进气道 遗传算法 数值模拟 

分 类 号：TJ760.33[兵器科学与技术—武器系统与运用工程]