한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제45권12호
  • /
  • Pages.1013-1020
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  • 2017
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  • 1225-1348(pISSN)
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  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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굽힘 하중에 의한 복합재료 파손 예측 연구

Failure Prediction for Composite Materials under Flexural Loading

  • 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 : 2017.08.03
  • 심사 : 2017.11.08
  • 발행 : 2017.12.01
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초록

본 연구에서는 굽힘 하중을 받는 복합재료 적층판에 대한 파손 강도를 예측하기 위하여 2D 변형률 기반의 파손 이론을 적용한 유한요소 해석을 수행하였다. 복합재료 적층판 내각 층의 파손 모드에 따른 강성저하를 고려하기 위해 점진적 파손 해석 방법을 적용하였다. 크로스 플라이와 준등방성 복합재 적층판에 대하여 3점 굽힘 시험을 수행하였다. 최대응력 이론, 최대 변형률 이론, 그리고 Tsai-Wu 파손 이론을 적용한 유한요소 해석을 수행하였다. 시험 및 파손 이론에 따른 해석 결과 비교를 통하여 2D 변형률 파손 이론의 정확성을 검증하였다.

In this study, the failure prediction of composite laminates under flexural loading is investigated. A FEA(finite element analysis) using 2D strain-based interactive failure theory. A pregressive failure analysis was applied to FEA for stiffness degradation with failure mode each layer. A three-point bending test based on the ASTM D790 are performed for cross-ply $[0/90]_8$ and quasi-isotropic $[0/{\pm}45/90]_{2s}$ laminated composites. The accuracy of the applied failure theory is verified with the experimental results and other failure criteria such as maximum strain, maximum stress and Tsai-Wu theories.

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참고문헌

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