Μηχανική συμπεριφορά προηγμένων αεροπορικών κραμάτων μαγνησίου

Abstract

Permanent objective of the aeronautical industry is the weight reduction of airframe, systems and interior components in order to increase operational capacity and reduce environmental impact via reduction of fuel consumption. In this frame, the utilization of low weight materials, like magnesium alloys, could represent a break through solution. Yet, the aeronautical application of magnesium alloys remains very limited due to the high corrosion susceptibility and the poor damage tolerance behaviour as compared to other structural alloys like aluminum and titanium. In the present work, a systematic investigation of the mechanical behaviour of two advanced rolled AZ magnesium alloys, namely AZ31 and AZ61, was conducted by taking into account the deformation mechanisms, damage accumulation mechanisms and failure mechanisms taking place in the microstructure of the materials. The present work mainly focuses on the fatigue behaviour of AZ31 alloy. Furthermore, the effect of prior corrosion damage on the mechanical behaviour has also been assessed. To accomplish the above objective a thorough experimental investigation was performed including microstructural characterization, tensile tests, constant amplitude fatigue tests and constant amplitude fatigue crack growth tests on both parent and pre-corroded specimens. The experimental results were supported by extensive metallographic and fractographic investigation. The tensile tests performed revealed anisotropy of the yield strength of the materials between rolling and transverse direction. The metallographic analysis has shown that the observed anisotropy is attributed to the near basal texture of the alloys and the angular spread of basal poles towards the rolling direction. Furthermore, the metallographic investigation indicates a clear variation in twinning density across the specimen length and the decisive role of twins in plastic deformation has been pointed out. Concerning the fatigue behaviour, it was observed that the S-N curves exhibit a very smooth transition from low to high cycle fatigue regime, indicating very high stress sensitivity on the fatigue life of the materials. Fatigue cracks in AZ31 alloy initiate in an early stage between strain incompatibility points (e.g. grain boundaries) due to difficulties in satisfying the von Mises criterion. As a result, the initiation and propagation mechanisms of the fatigue cracks are characterized as cleavage. In order to understand the fatigue mechanism of magnesium alloy AZ31 in the early stages of fatigue damage accumulation process, nano-indentation measurements at different percentages of the fatigue life of the AZ31 alloy have been performed and hardness alteration was obtained. The obtained results have shown that nano-hardness remains unchangeable with fatigue cycles until crack initiation. This has been interpreted as a lack of the material’s ability to accumulate damage in terms of cyclic plasticity at the early stages resulting in very early crack initiation. This is a major disadvantage for application where fatigue life is of primary importance. The mechanical tests on pre-corroded specimens have shown a significant degradation of the overall mechanical behaviour of the materials. Tensile properties degradation due to prior corrosion damage is attributed to the progressive notch effect of the developed pits, which increase locally the applied stress and in parallel reduce the ability of the material to accumulate large amounts of plastic deformation. In the case of cyclic loading the presence of corrosion pits results in the development of stress concentration, facilitating essentially the initiation and propagation of fatigue cracks. Concluding, the present work provides evidence that the major disadvantage of magnesium alloys for use in aeronautical structures is their fatigue behaviour, which is attributed to the hexagonal structure of magnesium, and secondarily the high corrosion susceptibility of magnesium which leads to significant degradation of the mechanical performance of the alloys.