Fatigue disbond growth in primary aerospace structures

A parametric finite element model incorporating virtual crack closure technique was developed in order to determine the critical disbond size and location for disbond growth in an adhesively bonded skin stiffened structure, subjected to uniaxial compression loading. The model was validated using static experimental tests on both pristine and artificially disbonded specimens. Three specimens were manufactured with critical initial disbonds based on the FE results and subjected to compression-compression fatigue loading at three different maximum loading amplitudes. Results of the fatigue testing showed significant disbond growth which resulted in substantial decreases in buckling loads.Aerospace EngineeringAerospace Structures & Material