experimental investigation of open-hole compression strength of carbon epoxy composite material and determination of localized strains using digital image correlation technique

The biggest application of the fiber-reinforced composites are in the field of military and commercial aircrafts. carbon fibers either alone or with the kevlar 49 fibers, are widely used as main material in many aero plane wing, fuselage and empennage components. composites materials have wide applications in different industries because of it has very different properties from the metals and polymers. in the drilling of carbon/epoxy composites the cut surface quality is very much dependent on the drilling parameters set during drilling which further effect the strength of the hole during extension/compression loading. in this research, carbon fiber epoxy composite material is drilled with the standard carbide drill bit and open hole compression (ohc) tests are performed on the universal testing machine. the digital image correlation (dic) technique is used to find out the strain distribution around the hole during compression loading. from the experimental method and dic, maximum strength of carbon epoxy composite is achieved by drilling at 1600-2400 mm/min in presence of notch. it was also observed that failure of the structure is dependent on the drilling feed rate and 1600-2400 mm/min was the optimized drilling range.