In the engineering design of modern wing panels and their optimal control system, the first step is to find and predict their dynamic characteristics. These characteristics are dependent on material properties, panel geometry, and boundary conditions. In addition, possible fracture existence, imperfections and environmental conditions may unpredictably change the frequency and modes shape of the panel and then the parameters of a control system. In the present paper, the effect of surface fracture depth and orientation on frequency and vibration mode switching of perovskite solar cells-based aircraft wing panels is investigated for the first time. The PSC (perovskite solar cell) panel is made of a polymer substrate reinforced with even-distributed graphene platelets (GPLs) and thin solar layers to enhance the overall electromechanical performance of the whole structure. Equations of motion of the panel are obtained by the Hamilton approach based on the properties of Reddy's third-order shear deformation theory and linear components of the Green-Lagrange strain tensor. The novel aspect is a line-spring model of surface crack by Cartmell et al. adapted to the model of the PSC panel under consideration. The discretization of the established equations of motion for the cracked panel is carried out by the element-free IMLS-Ritz method with mesh-free features. Validation of the obtained solutions is carried out by comparisons with results from previous studies for cracked laminated plates.

中文翻译：

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表面裂纹对太阳能航天结构频率和振动模式切换的影响

在现代翼板及其优化控制系统的工程设计中，第一步是找到并预测其动态特性。这些特性取决于材料特性、面板几何形状和边界条件。此外，可能存在的裂缝、缺陷和环境条件可能会不可预测地改变面板的频率和模态形状，进而改变控制系统的参数。在本文中，首次研究了表面断裂深度和方向对基于钙钛矿太阳能电池的飞机机翼板频率和振动模式切换的影响。 PSC（钙钛矿太阳能电池）面板由均匀分布的石墨烯片（GPL）和薄太阳能层增强的聚合物基板制成，以增强整个结构的整体机电性能。基于Reddy三阶剪切变形理论和Green-Lagrange应变张量的线性分量的性质，通过Hamilton方法获得了面板的运动方程。新颖的方面是 Cartmell 等人提出的表面裂纹线弹簧模型。适应正在考虑的 PSC 面板模型。通过具有无网格特征的无单元 IMLS-Ritz 方法对已建立的裂纹板运动方程进行离散化。通过与先前对裂纹层压板的研究结果进行比较来验证所获得的解决方案。