Flutter as a self-excited oscillation can cause catastrophic damage to the aircraft structure. Tuned mass damper (TMD) is one of the vibration suppression methods widely used in engineering. However, traditional linear aerodynamic methods are not accurate in transonic flow. In this study, we first establish an unsteady aerodynamic model of the NACA0012 airfoil using the system identification method based on the Auto-Regressive with eXogenous input (ARX) model. Then, a flutter suppression model is constructed by coupling the TMD with the aeroelastic system. The parameters of the TMD are investigated using the model-based aeroelastic stability analysis. It is found that the flutter instability mode of the original system has changed due to the participation of the TMD in the system modal coupling. The proposed reduced-order model (ROM) provides a fast stability analysis method for flutter suppression with TMD as well as significant guidance for TMD design and optimization.

中文翻译：

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基于模型的稳定性分析方法用调谐质量阻尼器抑制跨音速颤振

颤振作为一种自激振荡，会对飞机结构造成灾难性的破坏。调谐质量阻尼器（TMD）是工程中广泛使用的减振方法之一。然而，传统的线性气动方法在跨音速流动中并不准确。在这项研究中，我们首先使用基于自回归与外生输入（ARX）模型的系统识别方法建立了NACA0012翼型的非定常气动模型。然后，通过将 TMD 与气动弹性系统耦合构建颤振抑制模型。使用基于模型的气动弹性稳定性分析来研究 TMD 的参数。研究发现，由于TMD参与了系统模态耦合，原系统的颤振不稳定模态发生了变化。