The modeling of fiber metal laminates by thick shell elements

Finite element procedure for modelling fibre metal laminates

The effect of fatigue crack length on the residual strength of ARALL3 panels with fingertip doublers

Fatigue and residual strength tests were done on doubler specimens consisting of an ARALL3 (3/2) laminate with a bonded-on fingertip doubler. The primary objective was to determine the effect of fatigue crack length on the residual strenght and delamination onset stress for this type of specimen. The specimens were precracked to variable crack...

The effect of the environment on the fatigue properties of ARALL-3

The effect of the environment on the fatigue behaviour and residual strength of ARALL-3 has been studied using three types of specimens, varying in structural complexity. In addition to the reference ambient air condition, specimens were aged and/or fatigue loaded in hot/humid air or in sump tank fluid. Environmental fatigue loading of door...

The use of composite fracture models to describe the blunt notch behaviour of metal laminates

The blunt notch behaviour of metal laminates has mostly been described using concepts which were developed to describe the blunt notch behaviour of metals. In the current work the applicability of fracture models which were developed for composites to describe the blunt notch behaviour of metal laminates is assessed. It is shown that three...

Numerical simulation of free edge delamination in graphite-epoxy laminates under uniaxial tension

Fatigue damage in composites under different loading conditions

The damage development In notched (± 45, 0„, 90, 0-) carbon-epoxy coupon specimens tested under different loading conditions was determined. Constant amplitude tests at R = -1 and R = 0.1 as well as flight simulation tests were performed to establish those stress values for which no damage growth occurs.

The effect of sheet thickness and laminating on the fatigue resistance of the aluminium alloyd AL-7010T73651

The influence of sheet thickness (2 mm and 10 mm) and the influence of laminating (5x2 ram) on the fatigue crack growth properties of the aluminium alloy AL 7010-T 73651 were investigated. Both constant amplitude loading and flight simulation loading were applied. All 2 mm and 10 mm thick sheets were machined from a 150 mm thick plate, i.e....