Abstract
In this research, dynamic progressive failure of Glass-Fiber-Reinforced aluminum laminates under low-energy impact was modelled. Intralaminar damage models, strain-based damage evolution laws, Puck failure criteria were used in ABAQUS-VUMAT software for modelling. Bilinear cohesive model was used for interface delamination, and the Johnson-Cook models were employed for aluminum layers. Damage evolution behaviours of this hybrid composite were calculated. After that, energy dissipation mechanisms were examined to identify the progressive failure and delamination of composite layers and plastic deformation of aluminum layers. In order to determine stress intensity at crack tip, the analytical model for constant-amplitude fatigue crack propagation according to Paris law was applied. Also, bridging stress along crack length in aluminum layer was investigated by correlation between the delamination growth rate and energy release rate in hybrid composite layers. The obtained findings indicated that the highest amount of peak low velocity impact force belonged to Glare 4 3/2. The presented numerical method based on bridging stress phenomena can successfully be used for predicting the post impact fatigue life of Glare.
Highlights
A fiber metal laminate (FML) such as GLARE is a hybrid composite consisting of thin aluminum layer and fiberreinforced epoxy composite layer
It has been tried to model the response of FMLs
GLARE is a hybrid composite consisting of thin aluminum layer and fiber-reinforced epoxy composite layer
Summary
A fiber metal laminate (FML) such as GLARE is a hybrid composite consisting of thin aluminum layer and fiberreinforced epoxy composite layer. The most widely used metal for FML has been aluminum, and the fibers have been generally Kevlar or glass. FMLs with glass fiber (GLARE) and Kevlar fibers (ARALL) are used in aircraft structures [1,2,3,4,5] since they have several outstanding good points like weight saving, good impact resistance, and damage tolerance. GLARE laminate is a good candidate material for lots of applications in future aircraft structure, i.e. the fuselage, pressure bulkhead, tails and wings etc. Due to out of-plane loads, like impacts, FMLs may tolerate damage due to various mechanisms including: (i) plastic deformation of the metal layers; (ii) matrix cracking and fiber failure; (iii) delamination between composite plies; and (iv) debonding of the metal and composite layer. Considerable internal damages including little surface appearance are Alireza Sedaghat et al.: Numerical and Experimental Assessment of Post Impact Fatigue Life of
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