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首先介绍了国内外变体机翼和蒙皮结构的研究现状,提出了满足变体机翼蒙皮连续光滑以及大变形需求的波纹型复合材料蒙皮结构。建立了复合材料的密度、各相所占体积分数以及各向弹性模量的计算表达式。根据计算结果利用MSC.Patran/Nastran进行了有限元仿真分析。制备了平板型和波纹型蒙皮试验样件,并进行了样件拉伸试验。最后将仿真结果与拉伸实验进行了比较和分析,验证了仿真模型的正确性与波纹型蒙皮的大变形能力,为进一步的实验研究与蒙皮优化提供了依据。
First of all, the research status of variant wing and skin structure at home and abroad are introduced. The corrugated composite skin structure which meets the continuous smoothness and large deformation of the variant wing skin is proposed. The formulas for calculating the density of composites, the volume fraction of each phase and the modulus of elasticity were established. Based on the calculation results, finite element simulation analysis was performed by using MSC.Patran / Nastran. Flat and corrugated skin samples were prepared, and the sample tensile test was carried out. Finally, the simulation results were compared with the tensile test to verify the correctness of the simulation model and the large deformation capacity of corrugated skin, which provided a basis for further experimental research and skinning optimization.