超燃冲压发动机二维进气道多级多目标优化设计方法  

The Multi-level and Multiobjective Optimization Design Method for Two Dimensional Scramjet Inlet

作　　者：罗世彬[1] 罗文彩[1] 丁猛[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2004年第3期1-6,共6页Journal of National University of Defense Technology

基　　金：国家863基金资助项目;国防科技大学创新基金资助项目

摘　　要：提出了超燃冲压发动机二维进气道的多级多目标设计方法。选择总压恢复系数、压升比和阻力系数为性能目标,引入多级设计概念,分别基于一维气动力学分析方法和计算流体力学方法,采用混合遗传算法对4楔角外压和2楔角内压混合压缩进气道进行了多级多目标优化设计,得到了问题的Pareto非劣解集。采用上述方法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 multi-level and multiobjective optimization (MLMOO) design method for two-dimensional scramjet inlet was established. Total pressure recovery coefficient, static pressure rise and drag coefficient were selected as performance objective functions to form the multiobjective optimization problem (MOP) of the two-dimensional scramjet mixed compression inlet with 4 external compression ramps and 2 internal compression ramps. The concept of multi-level design was introduced into the inlet performance analysis, one dimensional analysis method and computational fluid dynamics (CFD) method were used on the different stages during the optimization design process. To avoid converging to local optimal solutions and using gradient information which was hard to reach for numerical simulation, a multiobjective hybrid genetic algorithm was employed to find Pareto-optimal solutions in one single run for the present MOP. Following the MLMOO design method, the higher performance scramjet inlet would be worked out steadily.

关 键 词：超燃冲压发动机 高超声速进气道 多目标优化 数值模拟 混合遗传算法 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]