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A numerical study on flow-induced instabilities of supersonic FG-CNT reinforced composite flat panels in thermal environments

机译：超音速FG-CNT增强复合材料平板在热环境中流动引起的不稳定性数值研究

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摘要

In this research, the aerothermoelastic behaviors of supersonic functionally graded carbon nanotube reinforced composite (FG-CNTRC) flat panels in thermal environments are scrutinized. The dynamic model of the FG-CNTRC flat panel is developed on the basis of the first-order shear deformation theory incorporating von Karman geometrical nonlinearity. The thermomechanical properties of carbon nanotubes and polymer matrix are assumed to be temperature-dependent. The aerodynamic pressure is calculated according to the first-order supersonic piston theory. Adopting the discrete singular convolution method, the equations of motion and boundary conditions are converted into a set of algebraic equations. Ample numerical results are presented to highlight the aerothermoelastic responses of the FG-CNTRC flat panel considering various influential parameters such as CNT volume fraction and distribution, boundary conditions, thermal environments, geometrical parameters and Mach number. The results reveal that CNT distribution and volume fraction play a key role in enhancing the aerothermoelastic responses of FG-CNTRC flat panels. It is also found that presence of the aerodynamic pressure plays an essential role not only in the onset of aerothermal buckling instability, but also in changing the vibration and buckling mode shapes of FG-CNTRC flat panels. (C) 2017 Elsevier Ltd. All rights reserved.
机译：在这项研究中，仔细研究了超声功能梯度碳纳米管增强复合材料（FG-CNTRC）平板在热环境中的气动热弹性行为。 FG-CNTRC平板的动力学模型是基于结合了von Karman几何非线性的一阶剪切变形理论而开发的。碳纳米管和聚合物基体的热力学性质被认为是温度依赖性的。根据一阶超音速活塞理论计算气动压力。采用离散奇异卷积方法，将运动方程和边界条件方程转换为一组代数方程。给出了充分的数值结果，以突出FG-CNTRC平板的热弹性响应，其中考虑了各种影响参数，例如CNT的体积分数和分布，边界条件，热环境，几何参数和马赫数。结果表明，CNT分布和体积分数在增强FG-CNTRC平板的热弹性响应中起着关键作用。还发现，空气动力压力的存在不仅在空气热屈曲不稳定性的发生中起着至关重要的作用，而且在改变FG-CNTRC平板的振动和屈曲模式形状方面也起着至关重要的作用。 （C）2017 Elsevier Ltd.保留所有权利。

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