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progressive Failure Analysis of Composite/Aluminum Riveted Joints Subjected to Pull-Through Loading

Chinese Journal of Mechanical Engineering 2023年第1期36卷 129-138页

作者： Yuxing Yang Yongjie Bao Xueshu Liu Jinlong Wang Fengming Du Marine Engineering College Dalian Maritime UniversityDalian116026China School of Automotive Engineering Dalian University of TechnologyDalian116024China

Out-of-plane mechanical properties of the riveted joints restrict the performance of the wing box assembly of airplane.It is necessary to investigate the pull-through performance of the composite/metal riveted joints in order to guide the riveting design and ensure the safety of the wing box assembly.The progressive failure mechanism of composite/aluminum riveted joint subjected to pull-through loading was investigated by experiments and finite element method.A progressive damage model based on the Hashin-type criteria and zero-thickness cohesive zone method was developed by VUMAT subroutine,which was validated by both open-hole tensile test and three-point bending test.Predicted load-displacement response,failure modes and damage propagation were analysed and compared with the results of the pull-through tests.There are 4 obvious characteristic stages on the load-displacement curve of the pull-through test and that of the finite element model:first load take-up stage,damage stage,second load take-up stage and failure stage.Relative error of stiffness,first load peak and second load peak between finite element method and experiments were 8.1%,-3.3%and 10.6%,respectively.It was found that the specimen was mainly broken by rivet-penetration fracture and delamination of plies of the composite laminate.And the material within the scope of the rivet head is more dangerous with more serious tensile damages than other regions,especially for 90°plies.This study proposes a numerical method for damage prediction and reveals the progressive failure mechanism of the hybrid material riveted joints subjected to the pull-through loading.

关键词： Composite/metal joints Riveted joints Pull-through test progressive damage model

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维普期刊数据库

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Thermo-mechanical properties of RTM-made carbon fibre/polyimide composite attaching collar under transient heating

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Chinese Journal of Aeronautics 2023年第3期36卷 393-405页

作者： Shengda JIANG Chuyang LUO Peng ZHANG Jianwen BAO Peipei CAI Xufeng XIA Shanghai High Performance Fibers and Composites Center(Province-Ministry Joint) Center for Civil Aviation CompositesDonghua UniversityShanghai 201620China AVIC Composite Technology Center Science and Technology on Advanced Composites LaboratoryBeijing 101300China Luoyang Optoelectro Technology Development Center Luoyang 471009China

This study focuses on the thermo-mechanical properties of Carbon Fibre/Polyimide Composite(CFPC)attaching collars under transient heating.The CFPC attaching collars were fabricated by a high-temperature resin transfer moulding process,and their thermo-mechanical properties under the conditions of simultaneous transient heating and bending load were investigated.The results show that the attaching collar tends to fail at 118% of the limit load.The failure mode includes the fracture of the connecting screws,local extrusion damage of the hole edges,and slight ablation damage at the outer plies.And there is no observable residual deformation in the composite attaching collar.Furthermore,considering that the material properties vary with temperature,a progressive damage model based on the sequential thermo-mechanical coupling method was established to study the failure mechanism of the attaching collar.Finally,the damage factor of the CFPC was calculated to assess the safety status of the attaching collar.The results show that the primary damage modes of the composite attaching collar are intralaminar failure,which mainly occurs at the heat insulation layer and the hole edges,and these slightly affect the structural bearing capacity.A good correlation between the experiment and FEA is obtained.The test methods and analysis models proposed contribute to the safety assessment of composite structures under transient heating.

关键词： Polyimide composites progressive damage model Resin transfer moulding Thermo-mechanical properties Transient heating

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维普期刊数据库

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Strength Prediction of Cruciform Specimen Under Biaxial Loading

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Transactions of Nanjing University of Aeronautics and Astronautics 2017年第3期34卷 286-295页

作者： Weng Jingmeng Wen Weidong Xu Ying Jiangsu Province Key Laboratory of Aerospace Power System State Key Laboratory of Mechanics and Control of Mechanical StructuresNanjing University of Aeronautics and Astronautics

In order to achieve a better understanding of failure behavior of cruciform specimen under different biaxial loading conditions,a three-dimensional finite element model is established with solid and interface elements.Maximum stress criterion,two Hashin-type criteria and the new proposed criteria are used to predict the strength of plain woven textile composites when biaxial loading ratio equals 1.Compared with experimental data,only the new proposed criteria can reach reasonable results.The applicability of the new proposed criteria is also verified by predicting the tensile and compressive strength of cruciform specimen under different biaxial loading ratios.Moreover,the introduction of interface element makes it more intuitive to recognize delamination failure.The shape of the predicted delamination failure region in the interface layer is similar to that of the failure region in neighboring entity layers,but the area of delamination failure region is a little larger.

关键词： cruciform specimen biaxial loading progressive damage model failure criteria biaxial strength

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维普期刊数据库

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