现代信息科技2026，Vol.10Issue(18)：188-193,198,7.DOI:10.19850/j.cnki.2096-4706.2026.18.034
基于分区耦合方法的大展弦比柔性机翼非线性颤振响应分析
Nonlinear Flutter Response Analysis of High-Aspect-Ratio Flexible Wings Based on Partitioned Coupling Method
摘要
Abstract
To accurately predict the flutter response of high-aspect-ratio flexible wings and analyze its influencing factors,this paper combines unsteady aerodynamics,structural dynamics,and Fluid-Structure Interaction(FSI).The open-source framework preCICE is adopted to integrate fluid and structural solvers,and a time-domain aeroelastic analysis method is established.The accuracy of the proposed method is verified through simulations of the two-dimensional FSI benchmark case Turek-Hron-FSI3,and the full transient flutter evolution process is reproduced for a high-aspect-ratio flexible wing.The results show that considering geometric nonlinearity and using C3D8I incompatible mode elements can control the simulation error of structural deformation within 0.1％.An increasing angle of attack enhances modal coupling and softens structural stiffness,thus significantly reducing the flutter speed.关键词
气动弹性/流固耦合/preCICE/计算流体力学/计算结构动力学/大展弦比柔性机翼/模态耦合Key words
aeroelasticity/fluid-structure interaction/preCICE/Computational Fluid Dynamics/Computational Structural Dynamics/high-aspect-ratio flexible wing/modal coupling分类
信息技术与安全科学引用本文复制引用
申宇阳..基于分区耦合方法的大展弦比柔性机翼非线性颤振响应分析[J].现代信息科技,2026,10(18):188-193,198,7.基金项目
国家重点研发计划(2025YFB3003400) （2025YFB3003400）
