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dc.contributor.authorYang, Chihdar Charles
dc.contributor.authorDan-Jumbo, Eugene
dc.contributor.authorKeller, Russell L.
dc.contributor.authorGarg, V.
dc.contributor.authorRaju, Salahuddin
dc.date.accessioned2019-03-18T22:18:48Z
dc.date.available2019-03-18T22:18:48Z
dc.date.issued2009-09
dc.identifier.citationYang, C., Dan-Jumbo, E., Keller, R., Garg, V., & Raju, S. (2009). Strain energy release rate analysis of adhesive-bounded composite laminate joints with a cohesive crack. Paper presented at the 24th Annual Technical Conference of the American Society for Composites 2009 and 1st Joint Canadian-American Technical Conference on Composites,, 1364-381.
dc.identifier.isbn978-161567603-3
dc.identifier.urihttp://hdl.handle.net/10057/15954
dc.description.abstractFiber-reinforced composites have been widely used in the aviation industry due to their light weight and high corrosion resistance. In many applications, bolted joints have been replaced by adhesive-bonded joints because of the weight penalty and corrosion problems associated with bolted joints. This paper presents an analytical model to determine the strain energy release rate of an adhesive-bonded single-lap composite joint with a prescribed cohesive crack within the bond line at the edge of the joint subjected to axial tension. A stress model is derived to determine the stress/strain distribution within the joint. In the stress model, the governing equations of displacements within the adherends are formulated using the first-order laminated plate theory. Based on the adhesive stress distributions, the equivalent crack tip forces are obtained and the strain energy release rate due to the crack extension is determined by using the virtual crack closure technique (VCCT). The modified specimen geometry from ASTM D3165 standard test is used in the derivation. The system of second-order differential equations is solved to provide the adherend and adhesive stresses using the symbolic computational tool, Maple 9. Experiments are conducted to obtain the joint strength. The predicted joint strengths are compared with the experimental joint strengths to show the application of the developed analytical model.
dc.language.isoen_US
dc.publisherAmerican Society for Composites (ASC) & Canadian Association Composites Structures and Materials (CACSMA)
dc.subjectLaminated composites
dc.subjectAdhesive joints
dc.subjectAnalytical models
dc.subjectBolted joints
dc.subjectCorrosion resistance
dc.subjectCrack tips
dc.subjectCracks
dc.subjectModels
dc.subjectStress concentration
dc.subjectAdherends
dc.subjectAdhesive bonded joints
dc.subjectAdhesive stress
dc.subjectAdhesive-bonded
dc.subjectAviation industry
dc.subjectAxial tensions
dc.subjectCohesive cracks
dc.subjectComposite joint
dc.subjectComposite laminate
dc.subjectComputational tools
dc.subjectCorrosion problems
dc.subjectCrack extension
dc.subjectEquivalent crack
dc.subjectFiber-reinforced composite
dc.subjectFirst-order
dc.subjectGoverning equations
dc.subjectJoint strength
dc.subjectLaminated plate theory
dc.subjectLight weight
dc.subjectSecond-order differential equation
dc.subjectSpecimen geometry
dc.subjectStandard tests
dc.subjectStress models
dc.subjectStress/strain
dc.subjectTip forces
dc.subjectVirtual crack closure technique
dc.subjectWeight penalty
dc.titleStrain energy release rate analysis of adhesive-bounded composite laminate joints with a cohesive crack
dc.typeConference paper
dc.rights.holderCopyright 2009 American Society for Composites (ASC) & Canadian Association Composites Structures and Materials (CACSMA)


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