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In this research we develop an algorithm for calculating damage accumulation for metal-composite joints using the example of a helicopter blade attachment. The degradation of the composite material properties is investigated, since operation of composites leads to decline in their main mechanical properties, namely, stiffness and toughness as a result of possible binder failure. Damage growth in fibre-reinforced composites is a very complex process due to their heterogeneity and anisotropy. Joints are one of the most vulnerable spots in an aircraft, so joint design should be a priority. Joints can fail for various reasons, for example, assembly stresses, stress concentrations, and technological deviations, which affect the strength of bolted joints. The paper uses computational methods described in the interdisciplinary theory of elasticity, structural mechanics, structural strength, materials science, and mechanics of structural failure of composite materials. This study is aimed at determining the optimal joint assembly to ensure the safe operation of the structure during a specified service life. |
