서지주요정보
Free-edge delamination in advanced composite laminates = 고등 복합재료 적층판의 자유경계단 층간분리에 대한 연구
서명 / 저자 Free-edge delamination in advanced composite laminates = 고등 복합재료 적층판의 자유경계단 층간분리에 대한 연구 / Dong-Min Kim.
저자명 Kim, Dong-Min ; 김동민
발행사항 [대전 : 한국과학기술원, 1991].
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등록번호

8001721

소장위치/청구기호

학술문화관(문화관) 보존서고

DAE 9102

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초록정보

The free-edge delamination in composite laminates results directly form the interlaminar stresses at the ply-interfaces and exposoed free-edge, and it reduces overall structural performance of laminates. In this study, various laminates with different fiber orientations and stacking sequences are analyzed and tested to investigate the modes of edge delamination, to develop a simple stacking method for the suppression of free-edge delamination and to understand the failure mechanism in thick laminates under compression-compression fatigue. Delamination tests on various laminates show that some laminates delaminate only by the effect of mode II interlaminar shear stress and the stress component also plays an important role on free-edge delamination even though it is zero at the free-edge. More attention should be paid to the effect of mode II interlaminar stress to predict free-edge delaminations adequately. Each mode of delamination shows differences on the delamination fracture surfaces. The PRS stacking (the disposition of plies to be symmetric with respect to the values of effective Poission's ratio in one half of the laminate) and the PRS sublaminate approach (the repeated stacking of Poisson's ratio symmetric sublaminates) are found to be very efficient stacking methods to suppress free-edge delamination in thin and thick laminates, respectively. Those methods do not require any computations and provide much safer stacking sequences. The delamination cracks in composite laminates under compression-compression fatigue load initiate due to the predominant effect of mode III interlaminar shear stress. The delamination cracks propagate, and then local buckling occurs at the delaminated plies. The delamination near the top and bottom surfaces is easier to grow than the delamination near the laminate mid-plane because of the constraint effect of adjacent plies on local buckling.

서지기타정보

서지기타정보
청구기호 {DAE 9102
형태사항 xiii, 163 p. : 삽도 26 cm
언어 영어
일반주기 부록 : 고등 복합재료의 층간압축강도
저자명의 한글표기 : 김동민
지도교수의 영문표기 : Chang-Sun Hong
지도교수의 한글표기 : 홍창선
학위논문 학위논문(박사) - 한국과학기술원 : 항공공학과,
서지주기 참고문헌 : p. 77-83
주제 Composite materials --Delamination
Composite construction --Fatigue
Fracture mechanics
Fibrous composites
복합 재료 --과학기술용어시소러스
파괴 역학 --과학기술용어시소러스
모드 2 --과학기술용어시소러스
임계 파괴 --과학기술용어시소러스
피로 파. --과학기술용어시소러스
Laminated materials
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