지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학위논문
- 저자정보
- 지도교수
- 곽재섭
- 발행연도
- 2014
- 저작권
- 부경대학교 논문은 저작권에 의해 보호받습니다.
이용수0
이 논문의 연구 히스토리 (4)
- 이 논문의 후속연구가 궁금하신가요?
- 연관 학술논문 또는 학술발표를 통해 보다 발전된 연구결과를 확인하실 수 있습니다.
- 이 논문의 연구 히스토리 확인하기
초록· 키워드
오류제보하기
The purpose of this study was to identify the characteristics of thermosetting composite materials and the optimum conditions of the helicopter blades molding process. The characteristics of thermosetting composite were investigated through the simulation and experiment.
As a results, The carbon-epoxy prepreg TSN125 used for helicopter blades had optimal molding temperature, 126℃. And this temperature was approaching required specifications that showed proper temperature at a fast curing point and efficiency.
The structural stability of the blade mold of SS400 material was confirmed by structure analysis. In the results of structure analysis, the deformation of mold was occurred as 0.03~0.2㎛. But the mold without structure deforms to over 60㎛. The maximum compressive stress of mold with structure was distributed as 0.402~1.18MPa. The tensile strength, as 0.191~0.367MPa, was higher than conventional material properties.
The dimension of mold and blade was evaluated by the 3-axis coordinate measurement machine of Hexagon lambda 706030. The dimensional errors was distributed within the range of tolerance. The mold measurement results to Y-axis length direction from the reference point has maximum (+) error 0.05mm at 1619.70mm and maximum (-) error 0.057 mm at 6619.70mm. The blade measurement results has maximum (-) error 0.1425mm at 1619.70mm and minimum (-) error 0.009mm at 6619.7mm point. At maximum (+) error part of mold, the blade showed the maximum (-) error. The change of thickness of blade was caused by shrinkage and pull of resin. Thus, the amount of Epoxy filled in cavity between mold and thermosetting composite materials affected the dimensional accuracy of blade.
As a results, The carbon-epoxy prepreg TSN125 used for helicopter blades had optimal molding temperature, 126℃. And this temperature was approaching required specifications that showed proper temperature at a fast curing point and efficiency.
The structural stability of the blade mold of SS400 material was confirmed by structure analysis. In the results of structure analysis, the deformation of mold was occurred as 0.03~0.2㎛. But the mold without structure deforms to over 60㎛. The maximum compressive stress of mold with structure was distributed as 0.402~1.18MPa. The tensile strength, as 0.191~0.367MPa, was higher than conventional material properties.
The dimension of mold and blade was evaluated by the 3-axis coordinate measurement machine of Hexagon lambda 706030. The dimensional errors was distributed within the range of tolerance. The mold measurement results to Y-axis length direction from the reference point has maximum (+) error 0.05mm at 1619.70mm and maximum (-) error 0.057 mm at 6619.70mm. The blade measurement results has maximum (-) error 0.1425mm at 1619.70mm and minimum (-) error 0.009mm at 6619.7mm point. At maximum (+) error part of mold, the blade showed the maximum (-) error. The change of thickness of blade was caused by shrinkage and pull of resin. Thus, the amount of Epoxy filled in cavity between mold and thermosetting composite materials affected the dimensional accuracy of blade.
목차
List of tables ⅲList of figures ⅵ1. 서 론 11.1 연구배경 및 필요성 11.2 국내외 연구동향 21.3 연구목적 42. 이론적 배경 52.1 열경화성 복합재 52.2 헬기용 블레이드 82.3 성형공정 113. 성형공정의 시뮬레이션 133.1 유동해석 및 결과 133.2 온도 분포 173.3 구조해석 및 결과 204. 실험 및 고찰 284.1 금형 치수 오차 284.2 블레이드 치수 오차 335. 결 론 37REFERENCES 39ABSTRACT 46
최근 본 자료
댓글(0)
0