弹性机翼静气动弹性数值研究  

INVESTIGATIONS OF CHARACTERISTICS OF STATIC AEROELASTICITY FOR ELASTIC WING

作　　者：朱世权[1] 李海元[1] 陈志华[1] 张辉[1] 

机构地区：[1]南京理工大学瞬态物理重点实验室,南京210094

出　　处：《工程力学》2017年第B06期326-332,共7页Engineering Mechanics

基　　金：江苏省研究生培养创新工程项目(KYLX16_0480)

摘　　要：基于计算流体力学/计算结构动力学(CFD/CSD)单向流固耦合计算方法,对0.4~1.6之间8种马赫数下大展弦比HIRENASD(High Reynolds Number Aero-Structural Dynamics)机翼进行了静气动弹性数值研究。通过求解基于结构化网格的三维可压N-S方程得到了机翼的气动特性,对气动载荷作用下的机翼进行结构响应分析,得到了机翼在流固耦合作用下的位移和应力等参数,结果表明机翼翼尖位移和机翼最大应力在音速前后发生了突变。可为相关大展弦比机翼的设计与分析提供参考。The static aeroelastic analysis of a large-aspect-ratio HIRENASD （High Reynolds Number Aero-Structural Dynamics） wing with Mach numbers between 0.4-1.6 is calculated, based on the one-way coupling method of computational fluid dynamics/computational structural dynamics （CFD/CSD）. The aerodynamic characteristics of the wing are obtained by solving the three-dimensional N-S equations based on structured grids, the structural response of the wing under aerodynamic loads is analyzed, and the displacement and stress of the wing under fluid-structure coupling are obtained. The results show that the displacement of wing tip and the maximum stress of wing have a step change before and after the speed of sound, which can provide a corresponding reference for the design and analysis of relevant large aspect ratio wings.

关 键 词：CFD/CSD 大展弦比机翼 静气动弹性 气动特性 结构响应 

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]