Innovative hybrid materials developed at Delft University of Technology (e.g., ARALL and GLARE) dramatically reduce life-cycle costs and offer a great opportunity for service life extension of legacy aircraft. Replacement or repair of damaged aircraft components requires high-strength composite materials with high tailorability, fatigue, and impact-damage resistance, all of which are offered by the advanced hybrid materials. In addition, a reliable fatigue-life evaluation methodology for hybrid structures of arbitrary layup, configuration, constituent materials, and geometry is necessary. An efficient computational framework is presented for simulation of fatigue fracture in fiber-metal laminates based on the homogenized laminate modeled with large shell elements and cohesive zone used to simulate crack propagation. The cohesive traction-separation relationship is calibrated against the analytical solution for the strain-energy release rate, which explicitly accounts for the effect of fiber bridging. Appropriate calibration of the cohesive energy results in approximately constant crack-growth rate, a characteristic for fiber-metal laminates, as well as an accurate distribution of bridging stresses for the considered crack and delamination configurations. The proposed methodology is illustrated by simulating an experimental test conducted on a large glass-laminate-aluminum-reinforced-epoxy panel subjected to a constant-amplitude fatigue loading.
Finite Element Modeling of Fatigue in Fiber–Metal Laminates
AIAA journal ; 53 , 8
2015
Aufsatz (Zeitschrift)
Englisch
Fatigue characterization of fiber/metal laminates
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