Composites Research

  • 제34권5호
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  • Pages.296-304
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  • 2021
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  • 2288-2103(pISSN)
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  • 2288-2111(eISSN)
한국복합재료학회 (The Korean Society for Composite Materials)
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고속 열 성형 유한요소해석을 활용한 CF/PEKK 열가소성 복합재 구조물 제작 공정 예측 및 검증

Evaluation of Stamp Forming Process Parameters for CF/PEKK Thermoplastic Composite Using Finite Element Method

  • Lee, Keung-In (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Choe, Hyeon-Seok (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Kwak, June-Woo (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Lee, Jun-Sung (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Ju, Hyun-Woo (Korea Aerospace Industries, Ltd.) ;
  • Kweon, Jin-Hwe (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Nam, Young-Woo (School of Mechanical and Aerospace Engineering, Gyeongsang National University)
  • 투고 : 2021.09.03
  • 심사 : 2021.09.30
  • 발행 : 2021.11.05
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초록

본 연구에서는 유한요소법(FEM)에 기반한 CF/PEKK 열가소성 복합재 고속 열 성형 해석을 수행하였고 제작 공정을 예측 및 검증하였다. 대표적인 L 형 구조물 모델에 대해 트리밍 여유에 따른 성형성을 응력, 두께, 주름분포를 분석하였다. 그 결과, 블랭크의 트리밍 여유가 증가할수록 구조물의 성형성이 향상하는 것을 확인하였다. 특히 두께 및 주름 분포 측면에서 해석 모델과 실험 결과를 비교하여서 고속 열 성형 모델의 타당성을 검증하였다. 제작된 구조물은 시차 주사 열량 분석법 및 이미지 분석법을 통해 결정화도와 기공률이 측정되었다. 제작된 열가소성 구조물의 전 영역 기공률은 평균 0.75%, 결정화도는 약 21%로 항공기에 적용 가능한 수치로 평가되었다. 따라서 본 연구를 토대로 열가소성 복합재 고속 열 성형 공정에 대해 효과적인 예측이 가능할 것으로 판단된다.

This study presented the evaluation of the stamp forming process for L-shape CF/PEKK thermoplastic composite using the finite element model. The formability of three different trimming allowances has been examined for representative product geometry. The results showed that those manufactured by high trimming allowance showed more excellent formability in those areas. Moreover, the effects of the trimming allowances on the stress, thickness, wrinkle distributions of thermoplastic composites fabricated with the stamp forming process were evaluated. The comparison of the simulation and experimental results for the thickness and wrinkle distributions proved the accuracy of the stamp forming model. The crystallinity of the composite was performed by differential scanning calorimetry (DSC). The void content of the composite was evaluated by matrix digestion. Then, the fabricated structure was characterized and achieved high quality in crystallinity and void content. Consequently, the presented FEM modeling shows excellent potential for application in the aircraft product design process. This pragmatic approach could efficiently offer a valuable solution for the thermoplastic composite manufacturing field.

키워드

과제정보

본 연구는 산업통상자원부의 재원으로 한국산업기술진흥원의 지원을 받아 수행한 2019년 해외수주연계 항공부품산업 공정기술개발 사업(P0010341_AFP와 OoA공정기술기반 단일통로 대형민항기용 4 m 이상급 복합재 주익 스킨-스트링거 일체형 모듈 및 3 m 이상급 열가소성 복합재 동체 모듈 개발)의 지원을 받아 수행된 연구 결과입니다.

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