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首页> 外文期刊>Composite Structures >Modeling, analysis, and control of MFC sandwiched laminate panel flutter with general layups and arbitrary boundary conditions
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Modeling, analysis, and control of MFC sandwiched laminate panel flutter with general layups and arbitrary boundary conditions

机译：具有常规铺层和任意边界条件的MFC夹层层压板颤振的建模，分析和控制

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摘要

In this paper, a new solution approach based on Lagrange multipliers is developed for aeroelastic panel flutter analysis of rectangular composite plates sandwiched by two Macro Fiber Composites (MFCs). The smart panel has general stacking sequences and subjected to the elastic edge restraints. By utilizing the assumed mode technique, the displacements and electric potentials are expanded using formerly determined mode shapes. Afterward, the potential and kinetic energies of the problem are achieved and by employing the Lagrange equation, the discretized equations of the motion are obtained. The supersonic aerodynamic load is modeled through the well-known piston theory and included within the equations by means of the non-conservative force term of the Lagrange equation. Deriving the equations is more simplified thanks to the orthogonality of the Legendre polynomials. Finally, the input voltage of the MFC actuator is determined through the proportional or velocity feedback control algorithms based on the sensor output. The capability and credibility of the proposed approach are confirmed by comparing the results with those achieved by the FEM. The method is used to investigate the effects of MFCs orientations on the panel flutter boundaries of smart plates.
机译：在本文中，基于拉格朗日乘数的一种新的解决方法被开发用于气动弹性板颤振分析矩形复合板，该矩形复合板被两个宏纤维复合材料（MFCs）夹在中间。智能面板具有一般的堆叠顺序，并受到弹性边缘约束。通过利用假定的模式技术，使用先前确定的模式形状扩展了位移和电势。之后，获得了问题的势能和动能，并且通过使用拉格朗日方程式，获得了运动的离散方程式。超音速空气动力载荷通过众所周知的活塞理论建模，并通过拉格朗日方程的非保守力项包含在方程中。由于勒让德多项式的正交性，方程的推导更加简化。最后，通过基于传感器输出的比例或速度反馈控制算法确定MFC执行器的输入电压。通过将结果与FEM所获得的结果进行比较，可以验证所提出方法的能力和可信度。该方法用于研究MFCs方向对智能板的面板颤动边界的影响。

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