Composites Research

The Korean Society for Composite Materials (한국복합재료학회)
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Study on Impact Damage Behavior of Sandwich Composite Structure for aircraft

항공기 적용 샌드위치 복합재 구조의 충격 손상 거동 연구

  • 박현범 (호원대학교 국방기술학부 항공정비기술학전공) ;
  • 공창덕 (조선대학교 항공우주공학과)
  • Received : 2012.10.23
  • Accepted : 2013.01.15
  • Published : 2013.02.28
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Abstract

In this study, low velocity impact analysis on composite sandwich structure was performed. Sandwich structure configuration is made of Carbon-Epoxy face sheets and foam cores. For validating study, the results of an experimental and a finite element method analysis were compared previously. From the finite element method analysis results of sandwich panel, it was confirmed that the results of analysis was reasonable. Impactor velocity to initiate damage was estimated, and in order to investigate the damage at the predicted velocity, impact analysis using finite element method was performed. According to the impact analysis results of sandwich panel, it was confirmed that the damage was generated at the estimated impact velocity. Finally, The comparison of the numerical results with those measured by the experiment showed good agreement.

본 연구에서는 복합재 샌드위치 적층판의 저속 충격 해석을 수행하였다. 샌드위치 구조 형상의 스킨은 탄소/에폭시(Carbon-Epoxy) 재질이 채택되었고 코어(Core)의 재질은 폼(Foam)이 적용되었다. 연구의 타당성을 입증하기 위해 관련 문헌에서의 연구 결과에서 제시한 실험 결과와 유한 요소 해석 결과의 비교가 선행되었다. 타당성 검증을 바탕으로 본 연구에서 손상이 시작되는 충격체의 속도를 평가하고, 예측된 충격 속도에서 충격 거동을 분석하기위해 유한요소법을 이용하여 충격 해석을 수행하였다. 샌드위치 복합재 적층판의 충격 해석 결과 예측된 충격 속도에서 손상이 발생함을 확인하였다. 최종 시편 시험 결과와 수치 해석 결과의 비교 값이 잘 일치함을 확인하였다.

Keywords

References

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