항공우주시스템공학회지 (Journal of Aerospace System Engineering)

  • 제11권5호
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  • Pages.13-19
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  • 2017
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  • 1976-6300(pISSN)
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  • 2508-7150(eISSN)
항공우주시스템공학회 (The Society for Aerospace System Engineering)
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2D 변형률 파손 이론을 이용한 복합재료의 굽힘 거동 해석

A Study on Bending Behaviors of Laminated Composites using 2D Strain-based Failure Theory

  • 김진성 (한국항공대학교, 항공우주 및 기계공학과) ;
  • 노진호 (한국항공대학교, 항공우주 및 기계공학과) ;
  • 이수용 (한국항공대학교, 항공우주 및 기계공학과)
  • Kim, Jin-Sung (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Roh, Jin-Ho (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Lee, Soo-Yong (School of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • 투고 : 2017.08.24
  • 심사 : 2017.09.29
  • 발행 : 2017.10.31
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초록

본 연구에서는 굽힘 하중을 받는 복합재료 적층판의 파손 해석을 위하여 2D 변형률 기반 파손 이론을 적용하였다. 복합재료 적층판의 비선형 기계적 거동을 모사하기 위하여, 선형 증분 접근 방식을 적용하고 단위 길이 적층판에 대한 점진적 파손 해석을 수행하였다. 크로스플라이 및 준등방성 적층 패턴에 대하여 3점 굽힘 시험을 수행하고 해석 결과와 비교 검증하였다.

In this study, the bending analysis of composite laminates using the classical laminated theory is investigated. A piece-wise linear incremental approach is employed to describe the nonlinear mechanical behavior of the composite laminates, and a 2D strain-based interactive failure theory is employed to predict the ultimate flexural loads. The 3-point bending tests are performed for cross-ply and quasi-isotropic laminates. The analysis results with the failure theory are verified by comparing the analysis findings to the experimental outcome.

키워드

참고문헌

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