Abstract The paper presents an extension of vortex particle methods (VPM) in the context of pseudo-three-dimensional (pseudo-3D) multi-slice coupled numerical model for complex aeroelastic interactions of thin-walled structures. The flow around immersed bodies is analysed using pseudo-3D VPM with boundary element discretisation. The existing coupled model performs the aeroelastic interactions of line-like flexible structures using rigid cross-sections; the deformation of the system is analysed using the natural vibration modes of beam elements. The novelty of the presented coupled model is the inclusion of 3D shell vibration modes for structural analysis within the existing framework. The structural equations are formulated at the mid-surface of the thin shell elements and solved in the modal coordinate system. The slice-wise pressures on surface panels are projected to the corresponding structural nodes. New positions and velocity of surface panels are calculated to satisfy the velocity boundary conditions for solving new surface vortex streets. The coupled method has been validated by identifying the critical flutter wind speed of a T-shaped cantilever system. Benchmarks aeroelastic flapping of different flexible plates are studied further. The vortex-induced vibration of a circular pipe and the ovalling oscillations in circular shells are simulated to show the applicability of the method. Finally, the aeroelastic response of a cantilever roof system is analysed under different incoming wind speeds.

中文翻译：

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用于薄壁结构气动弹性相互作用的伪 3D 涡流粒子方法的扩展

摘要 本文介绍了涡流粒子方法 (VPM) 在用于薄壁结构复杂气动弹性相互作用的伪三维 (pseudo-3D) 多层耦合数值模型背景下的扩展。使用具有边界元离散化的伪 3D VPM 分析浸入体周围的流动。现有耦合模型使用刚性横截面执行线状柔性结构的气动弹性相互作用；使用梁单元的固有振动模式分析系统的变形。所提出的耦合模型的新颖之处在于在现有框架内包含用于结构分析的 3D 壳振动模式。结构方程是在薄壳单元的中面制定的，并在模态坐标系中求解。表面面板上的切片压力被投影到相应的结构节点。计算表面面板的新位置和速度以满足求解新表面涡街的速度边界条件。该耦合方法已通过识别 T 形悬臂系统的临界颤振风速得到验证。进一步研究了不同柔性板的气动弹性拍打基准。对圆管的涡激振动和圆壳内的椭圆振荡进行了仿真，验证了该方法的适用性。最后，分析了悬臂屋顶系统在不同来风风速下的气动弹性响应。计算表面面板的新位置和速度以满足求解新表面涡街的速度边界条件。该耦合方法已通过识别 T 形悬臂系统的临界颤振风速得到验证。进一步研究了不同柔性板的气动弹性拍打基准。对圆管的涡激振动和圆壳内的椭圆振荡进行了仿真，验证了该方法的适用性。最后，分析了悬臂屋顶系统在不同来风风速下的气动弹性响应。计算表面面板的新位置和速度以满足求解新表面涡街的速度边界条件。该耦合方法已通过识别 T 形悬臂系统的临界颤振风速得到验证。进一步研究了不同柔性板的气动弹性拍打基准。对圆管的涡激振动和圆壳内的椭圆振荡进行了仿真，验证了该方法的适用性。最后，分析了悬臂屋顶系统在不同来风风速下的气动弹性响应。对圆管的涡激振动和圆壳内的椭圆振荡进行了仿真，验证了该方法的适用性。最后，分析了悬臂屋顶系统在不同来风风速下的气动弹性响应。对圆管的涡激振动和圆壳内的椭圆振荡进行了仿真，验证了该方法的适用性。最后，分析了悬臂屋顶系统在不同来风风速下的气动弹性响应。