采用流-固耦合算法研究了曲壁板在跨/超声速气流下的气动弹性特征。首先，给出了曲壁板的Von Kármán几何大变形运动方程，并对其进行了标准有限元离散。然后，简述了流动的控制方程、数值解法、动网格和流-固耦合方式。最后，对曲壁板的气动弹性响应进行了数值模拟和分析。结果表明弯曲造成壁板的初始气动载荷非零，使得其与平壁板的气动弹性特征大相径庭：稳定的曲壁板存在静气动弹性变形；马赫数为2时，曲壁板失稳后，其颤振负向峰值远大于正向峰值，且弯曲高度的增大会诱发混沌型的振动；马赫数为0.8和0.9时，曲壁板仅会发生正向变形；马赫数为1.2时，失稳后曲壁板的颤振中心偏向了负方向。所得结果为高速飞行器的壁板设计和颤振抑制提供了依据，所提算法可推广应用于其它气动弹性问题的数值分析。
Abstract
A fluid-structure coupling algorithm was used to analyze curved panel aeroelastic behavior in transonic and supersonic airflow. First, with the Von Karman’s large deformation theory, the governing equation of curved panel was presented, and it was discretized by the standard finite element method. Then, the governing equations of fluid, numerical method, moving mesh and fluid-structure coupling way were introduced briefly. Finally, numerical simulations and analysis were carried out to study aeroelastic behavior of curved panels. Results demonstrate that the curvature causes nonzero initial aerodynamic load on the panel, this brings about great different aeroelastic features for curved panels compared with flat panels. Static aeroelastic deformation exists for the curved panel in stable state. At Mach 2, asymmetric flutter is born for the curved panel lost stability. As the curvature height increases, chaotic flutter can be induced. At Mach 0.8 and 0.9, the curved panel shows only positive aeroelastic deformation. At Mach 1.2, with its stability lost, the curved panel flutters more violently in the negative direction. The results obtained could guide the panel design and flutter suppression for high performance flight vehicles. Also the presented algorithm could be extended to numerically analyze other aeroelastic problems.
关键词
壁板颤振 /
流-固耦合 /
气动弹性
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Key words
panel flutter /
fluid-structure coupling /
aeroelasticity
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