某型民机复合材料机翼下壁板开口补强及优化研究  

Open Hole Strengthening and Optimization Research on Composites Wing Panel of A Certain Civil Aircraft

作　　者：陈文俊[1] 赵鲁春[1] 李军[1] 

机构地区：[1]宜宾学院物理与电子工程学院,四川宜宾644000

出　　处：《机械研究与应用》2015年第4期64-66,共3页Mechanical Research & Application

摘　　要：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 request of wing structural design, the open hole in composites wing panel is inevitable. The structure of open hole strengthening on composites wing panel is analyzed in this paper, and a two-dimensional finite element model of composite materials which uses shell element is established by using software MSC. Patran ＆ Nastran. Through calculation and analysis in three different schemes, it is compared that the displacement and stress change of wing panel under the load, and the stress change of layers on various angles ; while the effect of strengthening method and layer angle on stress distribution is studied. The results show that the displacement and the maximum stress could be reduced by using stiffener strengthening, and the stress concentration could be avoided effectively; The maximum stress appears on when using the stiff- ener strengthening method; and stiffener strengthening should be selected in the optimized schemes of open hole strengthening, and avoid the -45°ply.

关 键 词：机翼下壁板 复合材料 开口补强 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]