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In the present paper, compressive behavior and failure mechanism of quasi-isotropic CFRP laminates with impact damage are studied numerically by a finite element method. The impact damage is modeled as a double-spiral-shape damage consisting of pairs of fan-shape delaminations and transverse cracks which links the delaminations above and below the lamina. Theresultsofthegeometricallynonlinearanalysisshowthat thepost-buckling behaviorcomprises threestages;buckling ofthin damaged portionsnear thesurfaces,buckling ofthewholedamaged area (through-thickness buckling)and globalbucking.Stress concentration in 0layerwascaused at thetransversedirectionagainst theload.Theenergyreleaseratedistributionwascalculatedby thevirtualcrack closuretechnique(VCCT)along thewholedelaminationtips.Theenergyrelease rate of the every transverse direction rapidly increased after through-thickness buckling of the damageportion.Theincreasing curves ofmaximum energyreleaseratewith increasing compressiveloadwellcorrelatedwiththerelationshipbetweenthecompression-after-impact(CAI)strength andthemodeIIinterlaminarfracturetoughnessofvariouslaminates.Thefinalfailureoftheimpact damaged laminates is probably caused by simultaneous growth of the all delaminations to the transversedirectionwhen theinterfaceoflaminates is not verybrittle.

A Study on Compressive Behavior and Failure Mechanism of Impact Damaged CFRP Laminates