Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Evaluation and certification of stamp forming process for commercial aircraft thermoplastic fuselage composite structures

민수항공기 열가소성 복합재 동체 부품개발을 위한 고속 열 성형 공정 평가 및 인증

  • Ji-Sub Noh (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Ho-Young Shin (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Min-Chan Jung (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Joon-Hyeok Hwang (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • June-Woo Kwak (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Hyun-Woo Ju (Korea Aerospace Industries, Ltd) ;
  • Jin-Hwe Kweon (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Young-Woo Nam (Department of Smart Drone Engineering, Korea Aerospace University)
  • 노지섭 (경상국립대학교 기계항공공학부) ;
  • 신호영 (경상국립대학교 기계항공공학부) ;
  • 정민찬 (경상국립대학교 기계항공공학부) ;
  • 황준혁 (경상국립대학교 기계항공공학부) ;
  • 곽준우 (경상국립대학교 기계항공공학부) ;
  • 주현우 (한국항공우주산업(주)) ;
  • 권진회 (경상국립대학교 기계항공공학부) ;
  • 남영우 (한국항공대학교 스마트드론공학과)
  • Received : 2022.11.28
  • Accepted : 2023.05.30
  • Published : 2023.06.30
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Abstract

This study established the stamp forming process conditions to develop thermoplastic composite fuselage parts for commercial aircraft. Initially, the blank size and shape, tensioner position, and pre-load were numerically optimized according to the wrinkle and uniformity of fabricated structures using AniForm software. Afterward, the determined stamp forming conditions were employed to fabricate the real structures for verification. Good agreement between experimental and numerical analysis in terms of wrinkle distribution and thickness uniformity was obtained. For further evaluation, the crystallinity and porosity of the fabricated structure were analyzed based on CMH-17 and Part 23 to consider the composite material certification system. As a result, the crystallinity of all components was more than 21 %, while the porosity was less than 2 %. This means that the fabricated composite components offer potential for the aircraft fuselage structure with a certificated manufacturing method.

본 논문에서는 민수항공기 열가소성 복합재 동체 부품을 개발하기 위해 부품 설계, 고속 열 성형 공정 기반 제작, 제작된 부품의 성형성을 평가하였다. 고속 열 성형 해석을 수행하여 Blank 크기 및 형상, Tensioner 위치 및 초기 하중 등을 고려한 최적 공정변수를 수립하였고, 이를 기반으로 실제 제작을 수행하였다. 제작된 부품의 주름 분포, 두께 균일성 등을 평가하여 유한요소해석 기반의 공정 예측 정확성을 검증하였다. 또한, 제작단계에서 복합재료 인증체계를 고려하기 위해 CMH-17, Part 23을 기반으로 제작된 부품의 결정화도, 기공률을 분석하였고, 그 결과 모든 부품에서 결정화도 21% 이상, 기공률은 2% 이하를 보였다. 이를 통해 본 논문에서 수행한 공정 및 제작된 부품은 실제 항공기 동체 구조에 적용될 수 있는 품질과 인증 적합성에 일부 부합하는 것으로 판단하였다.

Keywords

Acknowledgement

본 연구는 산업통상자원부의 재원으로 한국산업기술진흥원의 지원을 받아 수행된 연구 결과입니다(과제번호: P0010341). 본 연구는 과학기술정보통신부의 재원으로 한국연구재단의 지원을 받아 수행된 연구 결과입니다(과제번호: NRF-2017R1A5A1015311).

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