Fibre Metal Laminate Glare consists of thin aluminium layers bonded together with pre-impregnated glass fibre layers and shows an excellent fatigue crack growth behaviour compared to monolithic aluminium. The fibres are insensitive to the occurring fatigue loads and remain intact while the fatigue cracks occur in the aluminium layers. As a consequence, part of the load is transferred through the fibre layers instead of around the crack tip in the aluminium layers, reducing the crack growth rate. The major concept in this thesis is the stress intensity at a crack tip in the metal layers of a Fibre Metal Laminate being the factor determining the extension of that crack under cyclic loading. The stress intensity factor consists of a crack opening contribution of the far field stresses in the aluminium layers, similar to monolithic aluminium, and a crack closing contribution of the intact fibres in the wake of the crack. An analytical model has been developed based on the crack opening relations. Validation with a wide range of test data, reveals a good correlation between predicted and experimental crack growth rates, crack opening contours and delamination shapes

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Fatigue Crack Propagation and Delamination Growth in Glare

Analytical prediction model for fatigue crack propagation and delamination growth in Glare

Fatigue behaviour of carbon fibre-reinforced aluminium laminates

Fatigue crack growth properties of a GLARE3-5/4 fiber/metal laminate

Fabrication of high-stiffness fiber-metal laminates and study of their behavior under low-velocity impact loadings

An aramid reinforced aluminum-epoxy-laminate, ARALL, which contains a fatigue crack and a delamination zone is analyzed. It is assumed that the interlaminar shear forces between the aluminum and aramid/epoxy layers are transmitted along the delamination boundary. The aramid/epoxy layer of the laminate is considered a series of linear springs. The tensile stress in the aramid/epoxy layer and the stress intensity factor in the aluminum layer are found for various experimentally observed delamination shapes. A residual strength criterion based on the maximum tensile stress in the aramid/epoxy layer is applied and the analytical results are correlated with the available experimental data.

Delamination shape effects in aramid-epoxy-aluminum (ARALL) laminates with fatigue cracks

The response of the aramid reinforced aluminum-epoxy-laminate to uniaxial and biaxial fatigue loading has been investigated. The fracture process in the laminates propagates mainly in the form of cracks in aluminum layers, delaminations between the resin-rich and fiber-rich prepreg layers, splitting in prepreg layers and fiber fracture. Ultrasonic microscopy has been used to evaluate the shape and size of the damage zone. The ultrasonic images have been calibrated by means of SEM optical microscopy of the laminates with sequential removal of the layers. Microscopic eliminaton reveals a direct correlation between delimination, fiber fracture, and fatigue crack growth in the aluminum layer. The results of this investigation strongly suggest that the laminate resistance to tension-tension biaxial fatigue is superior to that under uniaxial loading conditions

Experimental investigation of fatigue crack growth behavior and damage mechanisms of fiber/metal laminates under uniaxial and biaxial loading

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Delamination shape effects in aramid-epoxy-aluminum (ARALL) laminates with fatigue cracks

Experimental investigation of fatigue crack growth behavior and damage mechanisms of fiber/metal laminates under uniaxial and biaxial loading