CAJ | 학술논문

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。
근거궤익결구설계요구，하벽판적층합판상개구시불가피면적。주요대민용비궤적궤익몽피하벽판개구보강결구진행분석，이용유한원분석연건MSC. Patran&Nastran건립이유복합재료유한원모형，모형채용각단원。통과계산분석，대비료미보강벽판、보편보강화가강근보강삼충불동적방안정황하，궤익몽피하벽판재외재하하적위이이급응력변화，급불동각도포층적각층응력변화，연구료보강방식급포층각도대궤익하벽판응력분포적영향。결과표명가강근보강능교호감소위이화최대응력，피면응력집중；재채용가강근보강방안시，-45°적포층방향상응력최대；재설계궤익하벽판개구보강방안시응진량선용가강근보강，병진량감소-45°방향적포층。
According to the request of wing structural design, the open hole in composites wing panel is inevitable. The struc-ture of open hole strengthening on composites wing panel is analyzed in this paper, and a two-dimensional finite element mod-el of composite materials which uses shell element is established by using software MSC. Patran&Nastran. Through calcula-tion 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 dis-tribution 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.