S弯进气道全自动优化设计  

Design of S-Shaped Inlet Fully Automatic Optimization

作　　者：张竞[1] 邵雪明[1] 曾丽芳 郑远 宋晓晨 

机构地区：[1]浙江大学无人机研究中心

出　　处：《工业控制计算机》2019年第6期78-80,共3页Industrial Control Computer

摘　　要：为提高S弯进气道的气动特性,针对一款S弯进气道提出一种优化设计方法。基于大规模数值计算建立了一套全自动优化方法:以提高总压恢复系数和降低总压畸变为优化目标,基于Isight搭建一个完整的S弯进气道优化平台,并结合参数化建模、网格自动生成技术、数值计算以及非支配排序遗传算法(NSGA-Ⅱ)对进气道进行多目标优化设计。结果表明,优化后的进气道中心线形状更平滑,横截面积变化较平缓。与原始进气道相比,优化后的进气道在设计马赫数处,总压畸变降低54%,总压恢复提高0.02%,气动性能明显提高,流场均匀性有所增加。另外,对于总压恢复,优化效果随着马赫数的增加而增大,总压畸变在所有计算马赫数下优化效果都很明显。This paper establishes a set of automatic optimization methods based on large-scale numerical simulation,total pressure recovery and distortion at the exit of the diffuser are considered as optimization objectives,combining with parametric modeling,grid automatic generation technology,numerical simulation and Non-dominated Sorting Genetic Algorithm Ⅱ.After current optimization,both the changes of center line and cross-sectional area are smoother.By analyzing the optimization results,the total pressure recovery raises 0.02%,and the total pressure distortion reduces 54% at designed Mach number.

关 键 词：S弯进气道 优化 总压恢复 总压畸变 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]