摘要
长桁与蒙皮之间的脱胶是复合材料加筋壁板主要的失效形式之一。首先对复合材料机翼结构长桁-蒙皮典型结构进行了三点弯曲试验,获得破坏载荷以及界面失效模式。然后基于ABAQUS建立三维有限元模型,采用内聚力模型模拟界面的破坏情况。有限元计算结果与试验结果吻合较好,验证了有限元模型的合理性。在此基础上,对长桁凸缘宽度方向采用渐变厚度设计,开展了其对长桁-蒙皮界面承载能力的影响分析。研究结果表明采用变厚度设计可以减缓长桁凸缘末端附近的刚度突变,降低长桁凸缘末端与蒙皮之间界面的面外载荷。凸缘变厚度设计可以有效避免长桁与蒙皮界面过早出现脱胶失效,长桁凸缘末端越薄,界面脱黏载荷越大。
Stringer-skin debonding was one of the most important failure models in stiffened composite panels.Three-points bending tests were performed on representative stringer-skin structure of composite wing to simulate the flange-skin interface behavior and to obtain the failure mode and failure load.A 3D finite element model was built by using ABAQUS software to simulate interface failure with cohesive zone model.Numerical results agree well with test data,which validate the rationality of the finite element model.Influence of variable flange thickness design on stringer-skin interface bearing capacity was studied further.Results show that sudden stiffness change and out-of-plane load between stringer flange and skin at stringer flange edge is reduced by variable thickness design.Early flange-skin debonding failure is restrained significantly by variable flange thickness design.Thinner thickness at stringer flange edge results in higher interface debonding failure load.
作者
王喆
成李南
柴亚南
陈向明
李新祥
张阿盈
WANG Zhe;CHENG Li-nan;CHAI Ya-nan;CHEN Xiang-ming;LI Xin-xiang;ZHANG A-ying(Aircraft Strength Research Institute of China,Xi’an 710065,China)
出处
《科学技术与工程》
北大核心
2020年第7期2913-2919,共7页
Science Technology and Engineering
基金
民用飞机专项科研(MJ-2015-F-038)
航空科学基金(20180923002)。
关键词
复合材料
三点弯试验
界面脱胶
变厚度设计
承载能力
composite
three-points bending test
interface debonding
variable thickness design
bearing capacity
