摘要
分层损伤是复合材料层合板结构最主要的损伤形式,其主要由于制造缺陷以及受到外力冲击而产生。本文对含圆形分层损伤复合材料层合板在弯曲载荷作用下的屈曲行为进行研究,首先利用RayleighRitz法对含圆形分层复合材料层合板进行二维模型建立,通过此理论模型可以计算出材料屈曲临界弯矩值以及在特定弯曲载荷下中心点的离面位移值。随后,采用三维数字图像相关方法对分层材料进行实验研究,得到了分层材料在弯曲载荷作用下的屈曲形貌以及其中心点的载荷—位移曲线。通过实验验证了理论的可行性与准确性,可用于对含圆形分层材料在弯曲载荷作用下屈曲临界弯矩以及中心点离面位移大小的初步估算。
Delamination has been a subject of major concern in engineering applications of composite laminates by manufacturing defects or an impact. In this paper we investigated buckling behavior of composite laminates containing embedded delamination with circular shape. Firstly we use Rayleigh-Ritz methods to create modeling of composite laminate with the circular delamination. Through theoretical analysis,the displacement of specimen surface will be counted when the bucking happens. The bending load-dispalcement curves can be calculated at an arbitrary bending load M. After the theoretical analysis,3D digital image correlation was used to measure the evolution of the deformation of the laminate during bending to structural failure and the resulting full-field displacement maps. The theoretical model results are in agreement with the expermental results. The theory proves to be accurate and can be used to evaluate the critical buckling load of delaminated composite laminates under pure bending.
作者
李峰
陈金龙
宫文然
LI Feng CHEN Jinlong GONG Wenran(Department of Mechanics, Tianjin University,Tianjin 300072 Tianjin Key laboratory of Modem Engineering Mechanics,Tianjin 300072)
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2016年第5期29-37,共9页
Aerospace Materials & Technology
