서지주요정보
스트링거 보강 복합적층 원통 판넬의 좌굴후 거동 해석 = Postbuckling analysis of stringer-stiffened laminated composites cyclindrical panels under compression
서명 / 저자 스트링거 보강 복합적층 원통 판넬의 좌굴후 거동 해석 = Postbuckling analysis of stringer-stiffened laminated composites cyclindrical panels under compression / 김조권.
발행사항 [대전 : 한국과학기술원, 1995].
Online Access 제한공개(로그인 후 원문보기 가능)원문

소장정보

등록번호

8005499

소장위치/청구기호

학술문화관(문화관) 보존서고

DAE 95007

휴대폰 전송

도서상태

이용가능(대출불가)

사유안내

반납예정일

리뷰정보

초록정보

The postbuckling behavior of stringer-stiffened composite cylindrical panels is studied analytically and experimentally. Progressive failure analysis is implemented for the prediction of failure characteristics and postbuckling ultimate load. For the progressive failure analysis, the maximum stress criterion is applied to the average stress in each layer of all the finite elements. The present study utilizes the formulation of geometrically nonlinear finite element procedure based on the updated Lagrangian description with the second Piola-Kirchhoff stress tensor and the Green strain tensor, and the eight node degeneated shell element for finite element for finite element modeling of the laminated shell structure. In modeling stringers, new scheme to analyze the global and the local buckling of the stiffened panel is introduced. Results of the nonlinear finite element method combined with the progressive failure scheme is compared with experimental results. Present finite element results with considering of progressive failure scheme shows good agreement with experiment in the buckling load, postbuckling ultimate load, failure and deformations. As the numerical examples, the postbuckling behavior of stringer-stiffened composite panels under compression is investigated from the initial load, through the buckling and to the final collapse. The buckling load tends to be affected by the bending stiffness in axial direction, but the postbuckling ultimate load has nothing to do with it. The location of Blade-type stringer does not affect the buckling load and the postbuckling ultimate load nearly. The panels with Blade-type stringer shows many shear failure on skin and stringer near the intersection of skin and stringer. The panels with Wide Flange-type stringer shows many shear failure on skin and stringer near the intersection of skin and web, and the intersection of web and flange. Shear failure concentrated on the side stringer by large deformation disables the panels from carrying additional loads, and the structure collapses immediately.

서지기타정보

서지기타정보
청구기호 {DAE 95007
형태사항 xiv, 173 p. : 삽화 ; 26 cm
언어 한국어
일반주기 부록 수록
저자명의 영문표기 : Zoh-Gweon Kim
지도교수의 한글표기 : 홍창선
공동교수의 한글표기 : 김천곤
지도교수의 영문표기 : Chang-Sun Hong
공동교수의 영문표기 : Chun-Gon Kim
학위논문 학위논문(박사) - 한국과학기술원 : 항공우주공학과,
서지주기 참고문헌 : p. 72-77
주제 Fibrous composites.
Fracture mechanics.
Finite element method.
Laminated materials.
좌굴. --과학기술용어시소러스
파괴 역학. --과학기술용어시소러스
유한 요소법. --과학기술용어시소러스
복합 재료. --과학기술용어시소러스
Buckling (Mechanics)
QR CODE

책소개

전체보기

목차

전체보기

이 주제의 인기대출도서