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根据机翼结构设计要求,下壁板的层合板上开口是不可避免的。主要对民用飞机的机翼蒙皮下壁板开口补强结构进行分析,利用有限元分析软件MSC.Patran&Nastran建立二维复合材料有限元模型,模型采用壳单元。通过计算分析,对比了未补强壁板、补片补强和加强筋补强三种不同的方案情况下,机翼蒙皮下壁板在外载荷下的位移以及应力变化,及不同角度铺层的各层应力变化,研究了补强方式及铺层角度对机翼下壁板应力分布的影响。结果表明加强筋补强能较好减小位移和最大应力,避免应力集中;在采用加强筋补强方案时,-45°的铺层方向上应力最大;在设计机翼下壁板开口补强方案时应尽量选用加强筋补强,并尽量减少-45°方向的铺层。
According to the design requirements of the wing structure, the opening of the lower panel laminate is inevitable. Mainly on the wing structure of civil aircraft wing skin opening reinforcement analysis, the use of finite element analysis software MSC.Patran & Nastran established two-dimensional composite finite element model, the model uses shell elements. Through the calculation and analysis, the displacement and stress changes of the wing skin under the external load under different external loads were compared with the three different schemes of the unreinforced wall, the patch reinforcement and the reinforcement. The stress changes of each layer, the reinforcement method and the effect of ply angle on the stress distribution of the wing lower wallboard are studied. The results show that the stiffener reinforcement can reduce the displacement and the maximum stress well and avoid the stress concentration. When using the stiffener reinforcement scheme, the stress in the direction of ply of -45 ° is the largest. Should be used to strengthen the tendons should be strengthened, and try to reduce the layer of -45 ° direction.