IMPLEMENTATION OF INTERLAMINAR FRACTURE MECHANICS IN DESIGN: AN OVERVIEW

摘要: SUMMARY: The state-of-the-art in the areas of delamination characterization, interlaminar fracturemechanics analysis tools and experimental verification life predictions is demonstrated usingskin/stringer debonding failure as an engineering problem to describe overall methodology. KEY TERMS: delamination, fracture toughness, computational mechanics, finite elementanalysis, virtual crack closure technique INTRODUCTION Many composite components aerospace structures are made flat or curved panels with co-curedor adhesively-bonded frames stiffeners. A consistent step-wise approach has been developed over thelast decade which uses experiments detect mechanism, stress todetermine location first matrix cracking mechanics investigate thepotential for growth. Testing thin skin stiffened designed aircraft fuselageapplications shown that bond at tip frame flange important very likelyfailure mode Figure 1 [1]. Debonding also occurs when a thin-gage fuselage panelis allowed buckle service. Comparatively simple specimens consisting stringer bondedonto have study skin/stiffener [2, 3] (Figure 2a). thatinitiates these (as 2b) identical failureobserved full-scale pull-off [1, 4].The objective this paper demonstrate delaminationcharacterization, lifepredictions. advances required all three order reach level maturity desired forimplementation methodology design certification arehighlighted. skin/stringer was selected demonstratethe