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• W649417086 abstract "This thesis consists of six papers within the area of composite fatigue and residual strength in aircraft structures. The dissertation is a mixture of experimental, numerical and theoretical work with focus on some structural hot-spots as defined in the certification process. Basic fracture mechanical properties were investigated, both numerically and experimentally for the standard DCB-and ENF-specimens, with respect to different ply interfaces and materials. Toughness measurements on specimens with non-zero interfaces have a considerable higher toughness than specimens with zero interfaces, due to the fact that the initial crack deviates from the original symmetrical crack plane. A good prediction between FE-calculations and beam data analysis methods could be obtained if the non-homogenous characteristics of specimens with non-zero interfaces was taken into account. The cyclic delamination growth rates increased rapidly with increased ∆G, raising doubts about the structural applicability of such growth laws. The problem is rather a threshold problem. The importance of repeated loading on composite structures with artificial delaminations is also demonstrated. The rule of interlaminar stresses with respect to damage initiation on notched and unnotched specimens were numerically investigated with an state-of-the-art hp-adaptive FE-technique and compared to some existing semi-analytical models. Though the number of initiation points for various quasiisotropic layups were found to be quite different the initiation strain, from a calculation point of view, was almost the same. Investigated semi-analytical models as formulated today were not able to cope with the complex stress-state occurring at free edges. A simplified approach for composite fatigue design is suggested. The methodology is based on fatigue failure functions established on a laminate level and thus the calculated uniaxial properties will reflect the overall behaviour of the laminate. To establish the fatigue failure functions, a given SN-curve for a multi-directional laminate is considered as a series of failure points where the failure in the short life-region essentially is assumed to be fibre fracture and in the long life-region is assumed to be controlled by matrix properties. An experimental investigation was also carried out regarding effects on resulting life for composite structures. Different elimination levels were considered on various load spectra and on constant amplitude block loading. Results revealed that the elimination level could be set to approximately 50% of the maximum load range. This means that considerable time and cost in structural verification testing can be obtained. Spectrum fatigue testing accounting for a characteristic number of cycles could be mapped on constant amplitude data which means that a life prediction methodology can be radically simplified. The so called soft inclusion theory and delamination buckling theory was investigated on impact damaged composite structures for residual strength prediction. The investigation was supported by FE-technique for determination of the stress distribution in the buckled state and for characterisation of the damaged region. It could be concluded that for low-energy impact, although with conservative assumptions on stiffness reduction, the soft inclusion theory is unconservative for residual strength prediction. In contrast the delamination buckling theory shows good agreement for various impact energy levels, thicknesses and layups." @default.
• W649417086 created "2016-06-24" @default.
• W649417086 creator A5073774318 @default.
• W649417086 date "1999-01-01" @default.
• W649417086 modified "2023-09-24" @default.
• W649417086 title "Fatigue and residual strength of composite aircraft structures" @default.
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