Abstract
A special open-hole sheet specimen of GLARE fiber-metal laminate was used to simulate mixed loading similar to the loading of a riveted hole in a real fuselage skin structure. The effect of cyclic tension and secondary bending loading was studied. The notch region was observed through a microscope in order to detect the first fatigue crack initiation during fatigue loading. The number of cycles prior to crack initiation was measured, and the crack growth rate in the surface layer of the laminate was evaluated. The specimens were subjected to fatigue damage investigation in the inner layers of the laminate after termination of the test. A significant effect of secondary bending on fatigue crack initiation and early crack growth was found. The experimental results are discussed in terms of local stress-strain conditions in the notch region evaluated by means of finite element calculation.
Highlights
Fiber-metal laminates are a family of structural aerospace sheet materials, as shown in Vogelesang et al [1], that consist of thin metal sheets alternating with adhesive layers reinforced by high strength fibers
The crack growth data can fit a linear dependence. This implies that crack growth rate v = da / dN was approximately constant in all performed tests
The first fatigue cracks were found in the upper surface layer subjected to the maximum cyclic resulting stress
Summary
Fiber-metal laminates are a family of structural aerospace sheet materials, as shown in Vogelesang et al [1], that consist of thin metal sheets alternating with adhesive layers reinforced by high strength fibers. GLARE 3 fiber-metal laminate is composed of aluminium alloy layers and pre-impregnated layers of cross-plied high strength glass fibers in an epoxy-resin matrix. GLARE 3 has been designed as an excellent material for the pressurized fuselage skin structure of large aircraft of the future. Since riveting of large sheets is still the most common joining technology for a fuselage structure, rows of rivet holes are subjected to the highest attention. Attention is paid to the effect of mixed tension and bending loading on fatigue crack initiation and early growth in an open-hole sheet specimen
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
