发表机构
Indian Institute of Technology Hyderabad（印度理工学院海德拉巴分校）
机构由 AI 辅助整理，请以论文原文为准。AI 中文总结
该研究提出了集成重构涡粒子法与有限元法的模块化气动弹性求解器$\texttt{VarFlExI}$，通过显式交错分区方案实现流固耦合，经水洞实验验证，可高效准确预测柔性升力面的双向流固耦合气动弹性响应。
AI 中文摘要
我们提出了$\texttt{VarFlExI}$（Variable Fidelity Unsteady Flow-FEniCS Exchange Interface，可变保真度非定常流-FEniCS交换界面），这是一款用于建模柔性升力面双向流固耦合（FSI）的模块化气动弹性求解器。该框架采用重构涡粒子法（rVPM）求解不可压缩纳维-斯托克斯方程，无需计算成本高昂的体积网格划分，同时支持使用$\texttt{FLOWUnsteady}$框架进行可变保真度的气动建模。在结构侧，采用有限元法对赖斯纳-明德林（Reissner-Mindlin）板公式进行离散化，并通过广义-α法进行时间积分，利用高斯-牛顿法在$\texttt{FEniCS}$框架内求解非线性平衡方程。流体与结构求解器通过显式交错分区方案耦合，确保非匹配界面上载荷与位移传递的虚功守恒。为适应气动载荷与几何的多表征特性，界面耦合通过公共中间界面采用独立的功保守力传递算子与反向几何传递算子。该框架通过水洞实验验证，可准确预测耦合气动弹性响应，而非对各组成求解器进行独立验证。无网格气动求解器的计算效率使模拟能以显著更低的计算成本开展，同时保持精度。该求解器还通过涵盖不同流工况、结构特性及耦合参数的敏感性分析与参数研究进行评估。
英文摘要
We present $\texttt{VarFlExI}$ (Variable Fidelity Unsteady Flow-FEniCS Exchange Interface), a modular aeroelastic solver for modeling two-way fluid-structure interaction (FSI) of flexible lifting surfaces. The framework employs a reformulated Vortex Particle Method (rVPM) to solve the incompressible Navier-Stokes equations without the need for computationally expensive volumetric meshing, while supporting variable-fidelity aerodynamic modeling using the $\texttt{FLOWUnsteady}$ framework. On the structural side, a Reissner-Mindlin plate formulation is discretized using the finite element method and integrated in time through the generalized-$α$ method, with the nonlinear equilibrium equations solved using a Gauss-Newton procedure within the $\texttt{FEniCS}$ framework. Fluid and structural solvers are coupled through an explicit staggered partitioned scheme, ensuring conservation of virtual work for load and displacement transfer across the non-matching interface. To accommodate the multi-representative nature of the aerodynamic loads and geometry, the interface coupling employs separate work-conservative force and reverse-geometry transfer operators via a common intermediate interface. The framework is validated against water-tunnel experiments, demonstrating accurate prediction of the coupled aeroelastic response rather than independent validation of the constituent solvers. The computational efficiency of the meshless aerodynamic solver enables simulations at significantly lower computational cost while maintaining accuracy. The solver is further evaluated through sensitivity analyses and parameter studies spanning different flow conditions, structural properties, and coupling parameters.
CommentsPreprint to be submitted to Elsevier
