Abstract
In the present chapter, the interfacialInterfacial fracture behaviorFracture behavior of a titanium-to-CFRPTitanium-to-Carbon Fiber-Reinforced Polymer (CFRP) adhesive jointAdhesive joint is investigated experimentally using the DCBDouble cantilever beam (DCB) and ENFEnd-Notched Flexure (ENF) test configurations. A potential application of this joint is in the wings of future large passenger aircraft. Four distinctive, industry-relevant manufacturingManufacturing approaches are proposed: co-bondingCo-bonding with and without adhesiveAdhesive; and secondary bondingSecondary bonding, using thermoset and thermoplastic CFRPCarbon Fiber-Reinforced Polymer (CFRP). The VARTMVacuum-Assisted Resin Transfer Molding (VARTM) technique is used for all of them. After manufacturingManufacturing, the panels are cut into test specimens. Because these specimens are too thin (approximately 2.4 mm thick), we stiffen them on both titanium and compositeComposite sides with two aluminumAluminum backing beamsBacking beam to ensure the titanium will not yield during the subsequent DCBDouble cantilever beam (DCB) and ENFEnd-Notched Flexure (ENF) tests. The DRS proposed in Chap. 2 is used to determine the fracture toughnessFracture toughness of the joint. As highlighted in the previous two chapters, this considers effects such as BECBending–Extension Coupling (BEC) and RTS induced by manufacturingManufacturing. The load-versus-displacement responses, fracture behaviorsFracture behavior during testing, and fracture toughnessFracture toughness performances of the four MOs under consideration are presented and compared.
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