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A Finite Element Approach for Inter-Laminar Damage of the Carbon Fiber Reinforced Polymer due to Impact

机译:碳纤维增强聚合物由于撞击型层间损伤的有限元方法

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Composites reinforced with carbon fibers are widely used in automotive, aviation, nautical, in the blades structure of the wind turbines. Composite structures shows outstanding mechanical properties at static and cyclic behavior but the impact damage represents a problem extensively studied because during and after impact local damage and interlaminar fissures occur which cannot be detected easy. As a result, the experimental and theoretical approach to impact behavior of composites is a method of diagnosis and prognosis of phenomena that develop as a result of shock stresses. The paper focuses on the finite element modeling of the composite plate made of twelve layers which are arranged at an angle of 45° to each other, thus obtaining a quasi-isotropic material. The impact of the plate with low energy was simulated, resulting the equivalent stresses von Mises, shear stresses and deformations of each layer. It was found that the variation of stresses von Mises on the thickness of plate is linear and the shape and magnitude of the delamination developed in each layer depend on the difference between stiffness of the successive layers and rigidity of the interface between layers. The FEM results were confirmed experimentally. The novelty of the paper consists of the plate modeling as a multilayers structure and the simulation of impact with low energy. It were analyzed the shapes of strains from each layer and compared with experimental results.
机译:用碳纤维增强的复合材料广泛用于风力涡轮机的叶片结构中的汽车,航空,航海。复合结构显示出静态和循环行为的出色机械性能,但冲击损伤代表了广泛研究的问题,因为在局部损伤和发生的局部损伤和内部裂缝中都无法轻易检测到。结果,复合材料的影响行为的实验性和理论方法是一种诊断和预后的现象,其由于休克应力而发展的现象。该纸张专注于由十二层制成的复合板的有限元建模,其彼此以45°的角度布置,从而获得准各向同性的材料。模拟了板坯的影响,产生了低能量的影响,导致等效的von误法,剪切应力和每层的变形。结果发现,压力在板的厚度上的应力vonmes是线性的,并且在每层中产生的分层的形状和大小取决于连续层的刚度与层之间的界面的刚度之间的差异。有组织结果经过实验证实。本文的新颖性包括作为多层结构的板材建模和模拟与低能量的影响。分析了从每层的菌株的形状并与实验结果进行比较。

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