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In this study, it was performed damage assessment and repair of small scale aircraft adopted oncomposite. This aircraft adopted the sandwich structure to skin of wing. This study aims to investigate the residualstrength of sandwich composites with nomex honeycomb core and carbon fiber face sheets after the open holedamage by the experimental investigation. The 4-point bending tests were used to find the bending strength, and theopen hole was applied to introduce the simulated damage on the specimen. The bending strength test results afteropen hole were compared with the results of no damaged specimen test. In addition, The damaged compositestructure was repaired using external patch repair method after removing damaged area. After that, this study presentscomparison results of the experimental investigation between the damaged and the repaired specimen. It was foundthat the bending strength of repaired specimen was recovered up to 95% of undamaged specimen. :               .          .                    . 4       ,         .            .                    .                  95%   .

A Study on 4 Point Bending Strength of Carbon/epoxy Face Sheet and Honeycomb Core Sandwich Composite Structure after Open Hole Damage