基于CFD/CSD的大展弦比机翼气动弹性分析  

CFD/CSD-based aeroelastic analysis of large aspect ratio wing

作　　者：景武[1] 王孜孜[2] 李宪开[2] 

机构地区：[1]海军驻沈阳地区航空军事代表室,沈阳110034 [2]沈阳飞机设计研究所,沈阳110035

出　　处：《沈阳航空航天大学学报》2012年第2期23-27,共5页Journal of Shenyang Aerospace University

摘　　要：大展弦比飞机在飞行过程中受气动载荷影响,其大展弦比机翼产生弯曲和扭转变形,这种弹性变形严重影响飞机的飞行性能和飞行安全,不能将此种飞机机翼当作传统的刚性机翼进行气动分析。针对一大展弦比机翼,采用气动/结构耦合分析方法,利用计算流体动力学(CFD)软件CFX和计算结构动力学(CSD)软件ANSYS联合求解,研究了在不同载荷情况下大展弦比机翼静气动弹性变形对机翼气动特性的影响。结果表明,大展弦比无人机机翼受载变形后升阻比降低,升力下降明显,阻力略有上升,机翼翼尖容易失速。The aerodynamic performance and flying safety of HALE （High Altitude and Long Endurance） UAVs are largely affected by the aeroelastic distortion of its large aspect ratio wing. Large aspect ratio wing of UAV is bended and twisted by the air load during flight and thus is not to be treated as a traditional rigid wing. The effect of static aeroelastic distortion to the aeroelasticity for a large aspect ratio wing under differ- ent load statuses is analyzed. The integrated design method combining aerodynamics with structural dynam- ics is adopted in this analysis using computational fluid dynamics （CFD） program CFX and computational structual dynamics （CSD） program ANSYS. The results show that the local angle of attack changs with re- duced lift and increased drag of the aeroelastic wing and the wingtip is liable to stall.

关 键 词：CFD/CSD 大展弦比 气动弹性 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]