基于纤维金属加筋民机壁板的压缩强度预测模型

Compressive strength prediction model of civil aircraft panel based on fiber reinforced Metal

基于力矩分配法,研究了受轴压载荷下纤维金属加筋民机壁板的屈曲分析理论,分析计算了该民机壁板的压缩强度,并提出了一个民机壁板后屈曲极限强度的理论预测模型。通过与民机纤维金属加筋壁板压缩强度破坏试验结果对比,发现模型理论预测值与试验值吻合较好,偏差为3.01%,所建强度预测模型的精准性得到查验。此外,利用有限元方法分析了纤维金属加筋民机壁板的屈曲及后屈曲承载能力,模拟了壁板的应力集中区和失效过程,结果表明该壁板出现局部屈曲后拥有理想的后屈曲受载能力。本研究能为加筋民机壁板构型的材料选取、工艺性能的提升及预测纤维金属民机加筋壁板压缩强度值提供一定理论依据及试验数据,并可在民机预研设计阶段替代壁板大型结构件压缩试验,减少预研试验的成本与周期。

Based on the moment distribution method,the buckling analysis theory of fiber-metal reinforced civil aircraft plate structure under axial compression load is studied,the compressive strength of the civil aircraft plate structure is analyzed and calculated,and a theoretical prediction model for the ultimate strength of the civil aircraft plate structure after buckling is proposed.By comparing with the compressive strength failure test results of fibermetal reinforced plate structure of civil aircraft,the theoretical predicted values of the model are in good agreement with the experimental values,with a deviation of 3.01%.The accuracy of the strength prediction model established is verified.In addition,the buckling and post-buckling load-bearing capacities of fiber-metal reinforced civil aircraft plate structure were analyzed by using the finite element method,and the stress concentration area and failure process of the plate were simulated.The results show that the plate structure have ideal post-buckling load-bearing capacities after local buckling.This study can provide some theoretical basis and experimental data for the material selection of reinforced civil aircraft plate structure configuration,the improvement of technological performance and the prediction of the compression strength value of fiber metal reinforced civil aircraft plate structure,and can replace the compression test of large structural parts of the plate structure and reduce the cost and cycle of the pre-research experiment in the stage of civil aircraft pre-research and design.