Abstract
Abstract A model single carbon fibre/epoxy composite geometry was subjected to cyclic loading at a maximum strain below the critical fatigue limit of the matrix material. The carbon fibres were pre-strained prior to incorporation in the resin to ensure that they were free of thermally induced compression stresses in the axial direction. A strain controlled cyclic experiment from 0 to 0.5% applied strain was performed up to a maximum life of 106 cycles. At discrete fatigue levels of 100, 103, 104, 105, 5×105 and 106 cycles the fibre normal stress distributions of a specified window of observation were obtained by means of remote laser Raman microscopy. The fibre normal stress distributions at each fatigue level were converted to interfacial shear stress (ISS) distributions from which important parameters, such as the maximum ISS the system could accommodate, the transfer length for efficient stress built up and the length required for the attainment of maximum ISS were obtained. The results showed that up to the level of full fibre fragmentation the main fatigue damage parameter that affected the stress transfer efficiency at the interface was the fibre fracture process itself.
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