复合材料层合板鸟撞损伤及吸能分析

发布时间：2018-03-19 15:15

本文选题：鸟撞　切入点：复合材料层合板　出处：《郑州大学》2017年硕士论文　论文类型：学位论文

【摘要】：随着复合材料设计制造的逐步发展与成熟,复合材料在各工业领域均有广泛应用,尤其越来越多的被应用于航空领域内飞行器中的零部件。在研究飞机强度的过程中,鸟撞是一个不可忽略的问题,因此需要对飞行器上不同结构的复合材料抗鸟撞性能进行分析研究。当前国内外学者主要借助有限元软件与试验相结合的手段探究鸟撞对飞行器不同结构的复合材料层合板板损伤影响。首先,本文在总结了国内外关于鸟撞方法及成果的研究现状基础上,利用非线性动力分析有限元程序LS-DYNA结合不同的计算方法(Lagrange、ALE、SPH)对鸟撞钢板进行了分析。并与Wilbeck实验进行了对比分析,可以为下文鸟撞复合材料层合板确定了合适的鸟体模型。然后,建立了鸟撞复合材料层合板模型,分析了层合板铺层,曲面结构,密度,鸟体的冲击速度,鸟体的入射角度等因素对复合材料层合板吸能方面的影响,研究了复合材料层合板内部每单层的基体失效与纤维失效的过程。并将仿真分析与试验进行了相关对比,仿真结果效果较好。最后,分析了飞机机翼前缘复合材料蒙皮结构损伤阻抗能力。一方面研究了无斜板,单斜板,双斜板三种前缘机翼蒙皮的鸟撞动响应过程,另一方面研究了双斜板结构下的蒙皮厚度与鸟体的入射角度对机翼蒙皮的破坏影响。通过本文以上分析结果,可以为飞机机翼前缘设计提供参考。
[Abstract]:With the gradual development of composite material design and manufacture the mature, composite materials have been widely used in the industrial field, especially more and more being used in aviation field in aircraft components. In the process of Aircraft Strength Research of bird strike is a problem that can not be ignored, so the need for aircraft composite materials with different structures the analysis of the performance of anti bird hit. The current domestic and foreign scholars mainly use the finite element software and experiment method of bird strike composite laminate plate damage effect on the aircraft structure. Firstly, this paper summarizes the current research status about bird based methods and results at home and abroad, by using the nonlinear dynamic finite element analysis program LS-DYNA with different calculation methods (Lagrange, ALE, SPH) on the bird strike plate are analyzed. And compared with Wilbeck experiment, can The following bird strike composite laminates to determine the appropriate bird model. Then, a bird impact composite laminate model of laminated composite plates, surface structure, density, the impact velocity of the bird, the bird of the incident angle and other factors on composite laminates can influence the absorption process. Study on the matrix composite laminate layer failure and internal single fiber failure. And simulation analysis were related to better results compared with experimental results of simulation. Finally, analysis of the skin structure damage resistance of wing leading edge composite material can force. On the one hand of the inclined plate, monoclinic plate, double inclined plate three a front wing skin of the bird impact dynamic response process, the angle of incidence of skin thickness and bird body double inclined plate structure under the influence of wing skin damage. On the other hand. Through the above analysis, for aircraft The wing front design provides reference.

【学位授予单位】：郑州大学
【学位级别】：硕士
【学位授予年份】：2017
【分类号】：TB33

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