Progressive Failure Evaluation of Composite Skin-Stiffener Joints Using Node to Surface Interactions and CZM  

作　　者：A.Sane P.M.Padole R.V.Uddanwadiker 

机构地区：[1]Department of Mechanical Engineering,Visvesvaraya National Institute of Technology,Nagpur,440010,India

出　　处：《Computer Modeling in Engineering & Sciences》2018年第5期281-294,共14页工程与科学中的计算机建模（英文）

摘　　要：T shaped skin-stiffener joint are one of the most commonly used structures in aerospace components.It has been proven in various studies that these joints are susceptible to failure when loaded in pull out conditions however,in specific applications these joints undergo pull loading.De-lamination/de-bond nucleation and its growth is one of the most common failure mechanisms in a fiber reinforced composite structure.Crack growth takes place due to the induced interlaminar normal and shear stresses between different structural constituents when a load is applied.In this study,Finite Element Analysis has been performed using cohesive contact interactions on a composite T-joint to simulate the pull out test conditions.A simplified shell based model coupled with CZM is proposed,which can evaluate the failure initiation and progression accurately with lesser computational efforts.The final failure occurred at a displacement of 4.71 mm at the computed failure load of 472.57 kgf for basic configuration.Computed Failure load for the padded configuration is 672.8 kgf and corresponding displacement is 4.6 mm.The results obtained by the proposed numerical model are validated by experimental results and it is observed that predicted failure displacements and failure load calculated were correlating reasonably well with the experiment.

关 键 词：Carbon fiber composite FE analysis T-JOINT COHESIVE zone modeling NODE to surface interactions 

分 类 号：TB3[一般工业技术—材料科学与工程]