In the current research, optimal locations on aircraft panels are thickened to delay the flutter occurrence. A standard square isotropic Aluminum panel of 12 × 12 in. is considered. In formulating the model, the Kirchhoff-Love hypothesis and the Von-Karman nonlinear strain-displacement relations are applied. The quasi-steady first-order piston aerodynamic theory is used to calculate the applied load and the aerodynamic heating effects are not considered. In deriving the nonlinear equations of motion, the four-node Bogner Fox-Schmit (BFS) rectangular plate element is considered and the modal transformation is applied to decrease the calculation time. An ad hoc optimization method is implemented to achieve the objectives of the current research. The thickness, location, and the number of elements represent the parameters of the objective function. Many combinations between the number of elements, the arrangement of these elements, and the thickening values substantially delayed the flutter occurrence. In some cases, the corresponding critical aerodynamic values could be more than the double of the critical aerodynamic value of the pristine panel. Finally, to some extent, the current proposed technique can replace the dominant multifaceted active flutter damping techniques, which are more complex and more expensive.

在当前的研究中，飞机板上的最佳位置被加厚以延迟颤动的发生。考虑使用12×12英寸的标准方形各向同性铝板。在建立模型时，应用了Kirchhoff-Love假设和Von-Karman非线性应变位移关系。采用准稳态一阶活塞空气动力学理论来计算所施加的载荷，并且不考虑空气动力学的热效应。在推导非线性运动方程时，考虑了四节点Bogner Fox-Schmit（BFS）矩形板单元，并进行了模态转换以减少计算时间。为了实现本研究的目的，采用了一种临时优化方法。元素的厚度，位置和数量代表目标函数的参数。元素数量，这些元素的排列以及增稠值之间的许多组合基本上延迟了颤动的发生。在某些情况下，相应的临界空气动力学值可能会超过原始面板的临界空气动力学值的两倍。最后，在某种程度上，当前提出的技术可以取代占主导地位的多面主动颤振阻尼技术，后者更加复杂且价格更高。