Abstract Bird strike analysis has been an essential work in aeroplane design and airworthiness assessment. This paper presents a numerical method to simulate the deformation and failure process of composite wing leading edges in bird impact events. First of all, constitutive models were proposed for each material that composed the front edge. Specially, the model for composite material has taken account for the nonlinear behavior, the strain rate dependency, as well as different failure modes. Employing the user subroutine program and the failure modeling techniques, numerical models were built for bird strike simulation. Then the model was validated through bird impact tests on two kinds of edge structure: a laminated one and a sandwich one. Numerical results of both structures show good agreements with the test observation, from the dynamic response to the ultimate failure characteristics. Based on the numerical method, optimal stacking sequences of each structure was found. The results show that the modeling method may help with the crashworthiness design of composite structures.

中文翻译：

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鸟击下复合材料机翼前缘失效建模

摘要 鸟击分析一直是飞机设计和适航性评估中的一项重要工作。本文提出了一种数值方法来模拟鸟类撞击事件中复合材料机翼前缘的变形和破坏过程。首先，为构成前缘的每种材料提出了本构模型。特别地，复合材料模型考虑了非线性行为、应变率依赖性以及不同的失效模式。运用用户子程序和故障建模技术，建立了鸟击仿真的数值模型。然后通过两种边缘结构的鸟类撞击试验验证了该模型：层压一种和夹心一种。两种结构的数值结果与试验观察结果吻合良好，从动态响应到最终失效特性。基于数值方法，找到了每个结构的最佳堆叠顺序。结果表明，该建模方法有助于复合材料结构的耐撞性设计。