Preparation And Mechanical Properties Of Fiber Metal Laminates

Under the curing process，fiber metal laminates are spolidified by usinghigh-strength metals (aluminum, titanium) layer and the reinforcing fiber layeralternately. FMLs has good mechanical properties，now there are a large number ofapplications in the Airbus A380and Boeing777’s wing and fuselage structure,which requires of its mechanical properties, especially strength and fatigueproperties have a clear understanding.. In this paper， a combination ofexperimental and finite element analysis method has been adopted to research andanalysis on FMLs, from the FMLs preparation process, the interfacial adhesionstrength, modulus and fatigue properties.First, This article completed preparation of FMLs under the laminate curingprocess and non-destructive testing was used on FMLs. Considering themechanical properties of metallic materials and fiber, the various componentmaterials of the FMLs have been clearlied. Then combined with laminate interfacebonding theory of each component material surface treatment, to improve thebonding effect of the laminate interface. Two FMLs (excluding film containingfilm) have been curinged by the control of curing temperature and pressure incuring molding lamination process. Then the use of insulation on FMLspost-processing, so that the residual stress between the layers have been alleviatedand the released. Finally, ultrasonic C-scan nondestructive testing on laminatesand found that a good bonding between the layers.Then the two kinds of FMLs have been studied by mechanical experiments.Shear test and T-peel test were tested to detect the adhesive strength of the twokinds of FMLs and found that FMLs interface with film adhesive strength higherstability is poor if the injury occurs. Basic mechanical properties of two FMLsmodulus of elasticity and tensile strength have been measured by tensile test;found to contain film of the laminate elastic modulus is slightly lower but thetensile strength is the same, there was significantly different between σ-ε of thetwo laminates. Two the FMLs’ fatigue life SN curve have been drawn through thefatigue test in the stress ratio of-1and0.1, found that the film’s existence butreduced the fatigue properties of the laminates.Finally, the situation that two FMLs tensile-way under static loading has beensimulated with element software Abaqus. determined the destruction location ofthe specimen and got the laminate overall modulus, tensile strength which wasclose to the experimental value and the σ–ε relationship by calculating thesimulation results. The finite element simulation results have been Imported into fatigue software MSC.Fatigue to predict the fatigue life of two FML in differentlevels of fatigue loads. The simulated and experimental results were In goodagreement.