Abstract

Ceramic matrix composites (CMCs) are interesting materials for aeronautic applications because of their good mechanical properties at high temperatures even under air. Contrary to bulk ceramics, CMCs have a non-brittle mechanical behaviour due to the high strength of fibres, and due to optimized fibre/matrix interactions after matrix multi-cracking. Interactions between fibres and matrix act mainly at the interface level. When fibres and matrix are debonded in a zone close to a matrix crack, bridging fibres slide with friction in the surrounding matrix. This friction is characterised by the interfacial frictional shear stress ( τ) and is the main phenomenon leading to energy dissipation during cyclic fatigue of CMCs. Internal friction evolutions measured from stress/strain loops during cyclic fatigue or static fatigue can be described by shear-lag models with a variation of the interfacial shear stress. For example to-and-fro slides of bridging fibres can lead to an interfacial wear and a decrease of the interfacial shear stress. For static fatigue, recession of interfaces is also a way to modify the interfacial shear stress during time. Hence internal friction is an interesting parameter to be measured on CMCs because it allows to follow the evolutions of fibre/matrix interactions during fatigue.

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