高性能计算支持的静气弹优化设计方法  

Approach of static aeroelasticity optimization supported by high-performance computing

作　　者：黄勇[1] 孟德虹[1] 罗振先 孙岩[1] 王运涛[1] 王晓军[2] 孙俊峰[1] HUANG Yong;MENG Dehong;LUO Zhenxian;SUN Yan;WANG Yuntao;WANG Xiaojun;SUN Junfeng(China Aerodynamics R&D Center,Mianyang 621000,China;Beihang Univerity,Beijing 00083,China)

机构地区：[1]中国空气动力研究与发展中心,绵阳621000 [2]北京航空航天大学,北京100083

出　　处：《民用飞机设计与研究》2020年第3期96-111,共16页Civil Aircraft Design & Research

摘　　要：为扩大国产超级计算机在国内航空航天工业领域的应用,面向大展弦比机翼气动结构综合优化设计的实际问题,基于具有大量工业应用和自主知识产权的CFD软件TRIP和CSD软件SiPESC,应用改进的三维类别/形状变换(CST)参数化方法、差分敏度并行计算策略和移动渐近线(MMA)等大规模优化算法,通过TRIP+SiPESC耦合气弹分析软件预测气动载荷,发展了一套机翼型架外形的优化设计方法。以CRM标模内插机翼为例,针对无弯扭的初始型架构型,以气动外形展向几何扭转分布和结构有限元模型一万个壳单元厚度为设计变量,实现1-g载荷气动优化和2.5-g载荷结构优化的综合;在不降升阻比、满足最大应力/位移的约束下,俯仰力矩系数改善近40%,针对本文假设材料和初定的尺寸参数,机翼减重近9%,验证了方法和软件的有效性。该方法直接采用产品级高保真的自主静气弹分析软件预测气动力/载荷,将计算资源耗费大的静气弹优化和设计变量/约束规模大的结构优化分治,有较好工程应用前景。To enlarge application of the domestic supercomputers in aerospace industry,an approach of optimization design for the wing jig-shape was developed to resolve practical problems from aero-structural design for high aspect ratio wing on these machines with the CFD software TRIP and the CSD software SiPESC,which have autonomous intellectual properties and abundant industrial applications.Highlight features about this approach are the modified three-dimensional CST parameterization,parallelized evaluation for design sensitivities with the finite difference,and utilization of the large-scale optimization algorithm such as the MMA.More important is the prediction of statically aeroelastic forces and loads,which is performed with the coupling software of TRIP and SiPESC.To exemplify its capability,aerodynamic shape and structural FEM of the CRM wing was modified as an initial jig-shape through the elimination of twist and dihedral angle,and the augment of quadrilateral elements at wing LE and TE.The geometric twist distribution and the thickness of surface elements in the FEM were employed as design variables with the number of 10000 around.Then the aeroelasticity optimization with 1-g load and the structural optimization with 2.5-g load were iterated to maximize the aerodynamic efficiency,and to minimize the structural weight.Primary results are the improvement of pitching moment coefficient of 40%without lessening of lift/drag ratio,and the weight reduction of 9%under the condition of maximum stress and displacement,which indicate that the approach and the software framework are feasible,even for more large-scale problem due to the product-level prediction capability of software and the divide-and-rule strategy in optimization process.

关 键 词：静气动弹性 优化设计 高性能计算 CRM模型 型架构型 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]