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Aeroelastic stability analysis of curved composite panels with embedded Macro Fiber Composite actuators

机译：嵌入式宏观纤维复合材料作动器的弧形复合板的气动弹性稳定性分析

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摘要

This work investigates the aeroelastic stability boundary of curved composite panels with embedded Macro Fiber Composite (MFC) actuators in the supersonic airflow. Prescribed voltages are statically applied to the MFC actuators, inducing a pre-stress field which results in an additional stiffness effect on the curved panels, thus changing the aeroelastic stability boundary of curved composite panels. The principle of virtual work is applied to develop the equations of motion for the nonlinear flutter of curved composite panels with embedded MFC actuators. The Von Karman large deflection panel theory and the first order quasi-steady piston theory are adopted in the formulation. The Newton-Raphson method is employed to determine the static aeroelastic deflection under the applied voltages, and an eigenvalue solution is adopted to predict the aeroelastic stability boundary of the curved panels. Numerical results show that the influence of the applied voltages is distinct for the curved composite panels with different curvatures. In addition, the lamination angles of the MFC actuator and the temperature elevations will also significantly affect the aeroelastic stability boundary of curved composite panels in the supersonic airflow.
机译：这项工作研究了在超音速气流中带有嵌入式宏纤维复合材料（MFC）执行器的弯曲复合材料面板的气动弹性稳定性边界。将规定的电压静态地施加到MFC执行器上，从而产生预应力场，从而在曲面板上产生附加的刚度效果，从而改变曲面复合板的气动弹性稳定性边界。虚拟工作原理适用于开发带有嵌入式MFC执行器的弧形复合板非线性颤动的运动方程。公式采用冯卡曼大挠度板理论和一阶准稳态活塞理论。采用牛顿-拉夫森法确定施加电压下的静态气动弹性挠度，并采用特征值解来预测弯曲面板的气动弹性稳定性边界。数值结果表明，所施加电压的影响对于曲率不同的弯曲复合板是明显的。此外，MFC执行器的层压角度和温度升高也会显着影响超声速气流中弯曲复合板的气动弹性稳定性边界。

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