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An experimental procedure has been performed in this work to characterise failure behaviour of braided fabric reinforced composite laminates subjected to flexural load. The material system used was carbon/epoxy. The laminated beams were made using eight layers of diamond braid reinforcement. Two braiding angles, i.e., 5° and 15°, were applied. Six beams with laminate arrangements of [5/5/5/5/5/5/5/5], [15/15/15/15/15/15/15/15], [5/5/15/15/15/15/5/5], [15/15/5/5/5/5/15/15], [5/5/15/15/5/5/15/15], and [15/15/5/5/15/15/5/5] were loaded under 4-point bending to their ultimate failure, where the braiding angle is measured with respect to the beam axis. Bending stiffnesses, ultimate bending strengths, and load-deflection curves of the tested beams were reported. It was found that all the bending failures of the laminated beams were initiated from their top surface inwards, as a consequence of an excessive compressive stress in the beam cross-section. Further evidence in failure mechanism was recognised through a matrix combustion and fabric peeling out technique. It was shown that after the bending test the only un-failed lamina in some of the laminates was its bottom surface ply. The evidence clearly indicates that the neutral plane in a laminated beam keeps shifting once a lamina in the laminate has failed. The failed lamina in the laminate can hardly sustain any additional load. Thus the present experiment confirms that a total stiffness discount should be adopted in the layer-by-layer progressive failure analysis of a laminated composite. Using this discount procedure, a simulation method is highlighted in the paper. The predicted load-deflection curves up to the third-ply failure agreed reasonably with the measured ones.

Bending Failure Characterisation of Laminated Beams with Braided Fabric Reinforcement