Video supporting the paper: Unsteady Non-linear Control Surface Modelling for Aeroservoelastic Applications

These two videos show the aeroelastic responses of flexible wings under rapid control surface deflections in the transonic regime (M=0.85). The aileron and spoiler deflections in the videos go from +5.7 degrees to -5.7 degrees in amplitude (with a -30 degrees offset for the spoiler). The videos are not real-time however (about two times slower). A fluid-structure interaction (FSI) framework coupling RANS-CFD and FEM models was used to obtain these simulations. These simulations were then used to validate the aeroelastic and aerodynamic models developed in the following paper: Lancelot, P., De Breuker, R. (2021). "Unsteady Non-linear Control Surface Modelling for Aeroservoelastic Applications". Journal of Aeroelasticity and Structural Dynamics. The FSI setup is also described in this paper.

本两段视频展示了跨音速工况（马赫数M=0.85）下，柔性机翼在操纵面快速偏转时的气动弹性响应。视频中副翼与扰流板的偏转幅值范围为+5.7°至-5.7°，其中扰流板额外带有-30°的初始偏移量。需说明，本视频并非实时播放（播放速率约为实际工况的二分之一）。本次仿真采用了耦合雷诺平均Navier-Stokes计算流体动力学（RANS-CFD）与有限元法（Finite Element Method, FEM）模型的流固耦合（Fluid-Structure Interaction, FSI）框架完成。上述仿真结果被用于验证下述论文中开发的气动弹性与空气动力学模型：Lancelot P、De Breuker R于2021年发表于《气动弹性与结构动力学学报》（Journal of Aeroelasticity and Structural Dynamics）的论文《面向伺服气动弹性应用的非定常非线性操纵面建模》（Unsteady Non-linear Control Surface Modelling for Aeroservoelastic Applications）。该流固耦合框架的搭建细节也在本论文中进行了阐述。