Investigation Of Tensile And Impact Behavior Of Fibre Metal Laminate

Nowadays,composite material as a kind of high quality material is widely applied in aerospace,military and civil engineering such as ship building area.Fiber metal laminates(FMLs)are hybrid structures consisting of metal sheets and fiber reinforced plastic layers.Due to the presence of metal sheets,this kind of material have excellent process ability and impact resistance.Moreover,the fiber reinforced plastic payers can improve the fatigue resistance performance of entire hybrid material.Glass reinforced aluminum laminates(GLARE),Glass reinforced steel laminates and carbon reinforced steel laminates are three important structure.They are applied in fuselage building,shipbuilding and military helmet,respectively.Before large-scale used of one type of material,the basic mechanical property is essential.Experimental and numerical analysis are two most important methods.Reasonable methodology is essential for researcher to do comprehensive,deep and efficient analysis.In this paper,the tensile test and impact performance of fibre metal laminates is analyzed.Besides,a efficient numerical methodology is employed to analyzed damage evolution and reveal the failure mechanism during tensile test or impact process.The following aspects have been researched in detail:The influence of surface mechanical attrition treatment(SMAT)on the tensile test performance of 2024 T3 aluminium have been investigated.The reasonable experimental parameter as well is presented.Here a cohesive finite element method(CFEM)is employed to investigate the tensile performance of multi-layer SMAT alloys.In our simulation,zero-thickness cohesive element is inserted into all adjacent elements,and the detail of cracks initiation,evolution and deflect at the interface have been studied.By parameter study of numerical,the influence of model parameters,normal direction strength and tangential direction strength in CFEM have been studied.Besides,The original thickness of 304 stainless steel(SS)layer in SMAT and reduced area proportion in multi-layer warm co-rolling bring different results on stretch performance,which are assessed in our simulation.SMAT aluminium laminate is introduced to the fabrication of GLARE.After tensile test and theoretical calculation,the results show that the SMAT aluminium can improve the yield strength of GLARE obviously.Then,the low-velocity impact response of GLARE is presented too.A numerical methodology including user material subroutine VUMAT for composite material,Johnson-Cook flow stress model and surface-based cohesive behavior for interface delamination analysis are carried out to simulate the history of response during low-velocity impact of GLARE plate.The damage progression of fiber reinforced layers,aluminum alloy layers and delamination in FML are analyzed,respectively.Based on numerical analysis methods,a methodology for numerical simulation of ballistic performance of hybridization with SMAT 304 stainless steel and a carbon fiber-epoxy composite layer is presented.In our simulations,not only the residual velocity of ballistic and deformation of laminate,but the damage evolution of steel layers,composite layer and the delamination between composites and steel layer are shown in the simulation too.Therefore,the failure mechanisms of ballistic impact of the hybrid material is presented very well.Because of the accuracy and efficiency of our numerical methodology,it is employed to predict the ballistic performance and design the structure of the other hybrid material.In conclusion,SMAT aluminium laminate is introduced to the fabrication of GLARE.Though the ultimate strength of GLARE is decreasing,the yield of GLARE is increase obviously.Through combination of many numerical methods,a numerical methodology for the impact performance of hybridization with metal and composites is presented.In the numerical model,the impact response,damage evolution of material is analyzed.