Aeroelastic flutter analysis for 2D Kirchhoff and Mindlin panels with different boundary conditions in supersonic airflow
Aeroelastic flutter analysis for 2D Kirchhoff and Mindlin panels with different boundary conditions in supersonic airflow
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超音速气流中不同边界条件的二维 Kirchhoff 和 Mindlin 面板的气动弹性颤振分析
DOI：
10.1007/s00707-014-1141-1
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发表时间：
2014-04
期刊：
影响因子：
2.7
通讯作者：
Zhi-Guang Song
中科院分区：
文献类型：
--
作者：
Feng-Ming Li;Zhi-Guang Song
对超声速气流中忽略和考虑剪切变形的二维壁板的气动弹性特性进行了解析研究。这两种类型的面板被称为Kirchhoff面板和Mindlin面板。提出了一种估算气动弹性结构系统颤振边界的方法。结构模型采用经典板理论和一阶剪切变形理论。非定常气动压力的计算采用超声速活塞理论。应用汉密尔顿原理建立了结构系统的运动控制方程。计算了气动弹性结构系统运动偏微分方程的精确解，得到了壁板的气动弹性模态，并与结构的真空固有模态进行了比较。验证了本文方法在气动弹性分析中的正确性。研究了不同边界条件下壁板的气动弹性特性，并计算了壁板的时间响应历程。此外，还对假设模态法在气动弹性分析中的精度进行了研究。得到并分析了一些有趣和有用的结果。
Aeroelastic properties of two-dimensional panels neglecting and considering the shear deformation in supersonic airflow are analytically investigated. The two types of panel are known as the Kirchhoff and Mindlin panels. A method for estimating the flutter bound of the aeroelastic structural system is proposed. The classical plate theory and the first-order shear deformation theory are used in the structural modeling. The unsteady aerodynamic pressure is evaluated by the supersonic piston theory. The governing equation of motion of the structural system is formulated applying Hamilton’s principle. The exact solution for the partial differential equation of motion of the aeroelastic structural system is calculated, and the aeroelastic modes (AEMs) of the panels are obtained and compared with the vacuo natural modes of the structures. The correctness of the present methodology used in the aeroelastic analysis is verified. Aeroelastic characteristics of panels with different boundary conditions are investigated, and the time response history of the panel is calculated using the AEMs obtained in this study. Moreover, the accuracy of the assumed mode method in the aeroelastic analysis is also researched. Some interesting and useful results are obtained and analyzed.
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影响因子：
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