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时间:2019-11-26
《基于代理模型的飞翼多目标气动优化设计》由会员上传分享,免费在线阅读,更多相关内容在学术论文-天天文库。
1、第45卷第2期航空计算技术Vol.45No.22015年3月AeronauticalComputingTechniqueMar.2015基于代理模型的飞翼多目标气动优化设计刘俊,宋文萍,韩忠华(西北工业大学翼型叶栅空气动力学国家级重点实验室,陕西西安710072)摘要:针对飞翼布局飞行器,采用雷诺平均N-S方程(RANS)计算流场,使用基于代理模型的多目标优化方法进行了同时考虑起飞性能和巡航性能的多点多目标气动优化设计。在设计过程中,将飞翼的平面形状、剖面形状及扭转角同时作为设计变量(共58个设计变
2、量),将提高起飞时的升力系数和提高巡航升阻比为设计目标,以起飞状态和巡航状态的力矩系数作为气动约束,并以飞翼平面面积不减和剖面厚度不减作为几何约束。通过采用基于Kriging模型的多目标优化方法,以较小的计算花费得到了较好的Perato前沿。取Pareto前沿中一个最优解与基准外形的性能进行了对比,结果显示,优化外形的性能较基准外形的气动性能得到全面大幅提高且所有约束得到严格满足。关键词:飞翼;优化设计;多目标;Kriging模型;Pareto前沿;N-S方程中图分类号:V211文献标识码:A文章编
3、号:1671-654X(2015)02-0001-05Multi-objectiveAerodynamicDesignOptimizationofaFlyingWingusingSurrogateModelLIUJun,SONGWen-ping,HANZhong-hua(NationalKeyLaboratoryofScienceandTechnologyonAerodynamicDesignandResearch,NorthwesternPolytechnicalUniversity,Xi′an7
4、10072,China)Abstract:Amulti-pointandmulti-objectiveaerodynamicdesignoptimizationwhichsimultaneouslycon-sideringthetaking-offperformanceandcruiseperformanceofaflyingwingisstudiedinthisresearch.Intheoptimizationprocedure,theflowaroundthewingissimulatedus
5、ingtheRANSsolver;theplanformshape,sectionshapes,andtwistangleofsectionshapesaretakenasdesignvariables,whichresultsin58designvariablesintotal;maximizingtheliftcoefficientattaking-offconditionandthelift-to-dragratioatcruiseconditionaretakenasthetwoobject
6、ives,whilethemomentcoefficientsatthetwooperatingcon-ditionsaretakenasconstraints,andtheplanformareaaswellasthethicknessofsectionsarealsotakenasconstraints.Althoughtherearealargenumberofdesignvariables,agoodParetooptimalfrontisob-tainedwithasmallnumbero
7、fcandidatedesignevaluationbytheuseofsurrogatemodelandasequentialupdatingstrategy.TheperformanceofashapearbitrarilyselectedfromtheParetofrontischeckedandcomparedwiththebaseline,itshowsthattheoptimizedshapeoutperformsthebaselineattheconcernedconditionswi
8、thalltheconstraintsfulfilled.Keywords:flyingwing;optimization;multi-pointandmulti-objective;Krigingmodel;Paretofront;N-Sequations引言[2-5]体布局、概念设计方面,主要是根据作者的经验进飞翼布局飞机相比常规布局飞机气动效率高、结行设计,并且采用估算公式或求解精度较低的流动控构重量轻,因而成为下一代大型民用客机的重点发展制方程计算气动性能。这
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