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Free vibration analysis of locally damaged aerospace tapered composite structures using component-wise models

机译：局部损坏的航空航天锥形复合结构的自由振动分析

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This work presents the free vibration analysis of tapered aircraft structures made of composite and metallic materials, with reference to global and local damage. A refined one-dimensional model, developed in the framework of the Carrera Unified Formulation, has been used to provide a detailed description of structures. Multicomponent aeronautical structures have been modeled adopting Lagrange polynomials to evaluate the displacement field over the cross-section. Each component has been described through the component-wise approach, with its own geometrical and mechanical characteristics. The effects of localized damage have been investigated, thanks to the accuracy of the layer-wise models adopted. The model has been assessed by comparing the results with classical FE models. The results show that the present approach provides an accurate solution for the free vibration analyses of complex structures and is able to predict the consequences of a global or local failure of a structural component. The computational efficiency and the accuracy of the model used in this work can be exploited to characterize the dynamic response of complex composite structures considering a large number of damage configurations.
机译：这项工作提出了由复合材料和金属材料制成的锥形飞机结构的自由振动分析，并参考了整体和局部损坏。在Carrera统一公式框架内开发的精制一维模型已用于提供结构的详细描述。已经采用拉格朗日多项式对多组分航空结构进行了建模，以评估横截面上的位移场。每个组件已通过基于组件的方法进行了描述，并具有自己的几何和机械特性。由于采用的分层模型的准确性，已经研究了局部损坏的影响。通过将结果与经典有限元模型进行比较来评估该模型。结果表明，本方法为复杂结构的自由振动分析提供了一种精确的解决方案，并且能够预测结构部件整体或局部失效的后果。可以利用这项工作的模型的计算效率和准确性来表征考虑大量损伤配置的复杂复合结构的动力响应。

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