The viability of a method for determining the fatigue life of composite rotor hub flexbeam laminates using delamination fatigue characterization data and a geometric non-linear FE analysis (finite element) was studied. Combined tension and bending loading was applied to non-linear tapered flexbeam laminates with internal ply drops. These laminates, consisting of coupon specimens cut from a full-size S2/E7T1 glass-epoxy flexbeam were tested in a hydraulic load frame under combined axial-tension and transverse cyclic bending loads. The magnitude of the axial load remained constant and the direction of the load rotated with the specimen as the cyclic bending load was applied. The first delamination damage observed in the specimens occurred at the area around the tip of the outermost ply-drop group. Subsequently, unstable delamination occurred by complete delamination along the length of the specimen. Continued cycling resulted in multiple delaminations. A 2D finite element model of the flexbeam was developed and a geometrically non-linear analysis was performed. The global responses of the model and the test specimens agreed very well in terms of the transverse flexbeam tip-displacement and flapping angle. The FE model was used to calculate strain energy release rates (G) for delaminations initiating at the tip of the outer ply-drop area and growing toward the thick or thin regions of the flexbeam, as was observed in the specimens. The delamination growth toward the thick region was primarily mode II (shear), whereas delamination growth toward the thin region was almost completely mode I (opening). Material characterization data from cyclic double-cantilevered beam tests was used with the peak calculated G values to generate a curve predicting fatigue failure by unstable delamination as a function of the number of loading cycles. The calculated fatigue lives compared well with the test data.
Fatigue life methodology for tapered composite flexbeam laminates
Eine Lebensdauervorhersagemethode für sich verjüngende elastische Laminat-Träger
Journal of the American Helicopter Society ; 43 , 2 ; 146-155
1998
10 Seiten, 21 Bilder, 2 Tabellen, 22 Quellen
Article (Journal)
English
Hubschrauber , Rotor (Drehflügel) , Nabe , Biegeträger , Verbundkonstruktion , Dauerfestigkeit , Aufblättern (Schicht) , Finite-Elemente-Methode , nichtlineare Gleichung , Zuverlässigkeitsvoraussage , Epoxid , Glasfaserverstärkung , experimentelle Untersuchung , Versuchsanordnung , Axialbelastung , Torsion , Biegebeanspruchung , Rissbildung
Fatigue Life Methodology for Tapered Composite Flexbeam Laminates
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