Modeling aerothermoelastic properties and active flutter control of nanocomposite cylindrical shells in supersonic airflow under thermal environments
Modeling aerothermoelastic properties and active flutter control of nanocomposite cylindrical shells in supersonic airflow under thermal environments
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模拟热环境下超音速气流中纳米复合材料圆柱壳的气动热弹性特性和主动颤振控制
DOI：
10.1016/j.cma.2017.07.014
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发表时间：
2017-10
影响因子：
7.2
通讯作者：
Liew K. M.
中科院分区：
文献类型：
--
作者：
Zhang L. W.;Song Z. G.;Liew K. M.
我们研究了圆柱形纳米复合材料（即碳纳米管增强复合材料）壳体在热环境下超音速气流中的气动弹性行为。同时，利用压电材料对复合材料圆柱壳进行了颤振主动控制。将Reddy高阶剪切变形理论应用于结构建模，根据几何变形关系推导出压电片的位移场。利用汉密尔顿原理建立了系统的运动偏微分方程，并采用假设模态法对其进行离散。采用位移反馈和线性二次型调节器（LQR）方法设计主动控制器。采用频域法分析了圆柱壳的气动热弹性特性。采用三阶剪切变形理论（TSDT）计算了圆柱壳的颤振边界，并与一阶剪切变形理论（FSDT）进行了比较，以验证高阶剪切变形理论在厚纳米复合材料结构振动分析中的必要性。研究了温度变化、碳纳米管分布和碳纳米管体积分数对复合材料圆柱壳气动弹性稳定性的影响。比较了不同控制方法的颤振主动控制效果。研究了圆柱壳厚度对颤振控制效果的影响。
We examine the aeroelastic behavior of a cylindrical nanocomposite (i.e. CNT-reinforced composite) shell in a supersonic airflow under thermal environments. Meanwhile, using piezoelectric materials, active flutter control of the cylindrical nanocomposite shell is conducted. Reddy’s high-order shear deformation theory is applied in the structural modeling, and the displacement fields of piezoelectric patches are derived according to the geometrical deformation relationship. The partial differential equation of motion is formulated by way of Hamilton’s principle and then is discretized by the assumed mode method. The active controller is designed by the displacement feedback and linear quadratic regular (LQR) methods. The aerothermoelastic properties of the cylindrical shell are analyzed using the frequency-domain method. The flutter bounds of the cylindrical shell are computed using the third-order shear deformation theory (TSDT), and the first-order shear deformation theory (FSDT) is compared in order to verify the necessity of the high-order shear deformation theory in the vibration analysis of thick nanocomposite structures. The influences of temperature change, CNT distribution and CNT volume fraction on the aeroelastic stability of the nanocomposite cylindrical shell are investigated. The active flutter control effects of different control methods are performed. The influence of thickness of the cylindrical shell on the flutter control effects is examined.
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DOI：
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发表时间：
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期刊：
Journal of Modeling in Mechanics and Materials
影响因子：
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