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http://dx.doi.org/10.5139/JKSAS.2021.49.7.549

Compressive Strength Prediction of Composite Laminates Containing Circular Holes  

Kim, Sung Joon (Korea Aerospace Research Institute)
Park, Sehoon (Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.49, no.7, 2021 , pp. 549-555 More about this Journal
Abstract
Open hole strength of composite laminates is often used as the design allowable strength for designing composite aircraft structures, particularly those structures subjected to impact loading. Generally, the degradation of strength due to a barely visible impact damage (BVID) is assumed as the strength of 6.0 mm hole diameter in 24.0 mm width specimen. In this study, the residual strength static tests of composite laminates containing circular holes have been performed to investigate the effects of fiber orientation structure on open hole strength. The point stress criterion using a characteristic length is used to predict the open hole strength. The finite element analysis has been used to validate the analytical method. From the test results, it is shown that the characteristic length is related to the percentage of 0°, ±45° and 90° plies of the laminate. And regression analysis has performed to determine the characteristic length and strength of no hole specimens on the arbitrary layup pattern.
Keywords
Design Allowables; Residual Strength; Point Stress Criterion; Characteristic Length; Regression Analysis;
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