복합재 내압선체의 적층에 따른 좌굴하중 변화에 관한 유한요소 해석

Finite Element Analysis on Buckling Pressure by the Lamination of Composite Pressure Bull

  • 손정윤 (넥센타이어(주)) ;
  • 조종래 (한국해양대학교 기계정보공학부) ;
  • 배원병 (부산대학교 기계공학부) ;
  • 권진회 (경상대학교 기계항공공학부) ;
  • 최진호 (경상대학교 기계항공공학부) ;
  • 조윤식 (국방과학연구소 2체계 개발본부) ;
  • 김두기 (국방과학연구소 2체계 개발본부)
  • 발행 : 2005.05.01

초록

This paper deal with the optimal lamination condition of cylindrical shell applied new composite URN300 for a study of composite empirical formula. Finite element analyses for isotropic materials considered element numbers and boundary conditions are compared with existing empirical formulas to apply FE analysis for composite. And composite tensile test is done to know the composite material applied FE analysis for composite. The results of FE analyses for isotropic materials have indicated that Optimal element number and boundary condition were 1600 and both simple support. These conditions were applied in composite FE analyses. Ply orientations and lamination patterns in FE analyses for composite were considered. Ply orientations are $0^{\circ},\;15^{\circ},\;30^{\circ},\;45^{\circ},\;60^{\circ},\;75^{\circ},\;and\;90^{\circ}$. Lamination patterns are $[\pm\theta/0/90]_{14s]$ and $[\pm\theta_{14}/0_{14}/90_{14}]_s$ in FE analysis. Lamination pattern $[\pm\theta_{14}/0_{14}/90_{14}]_s$ is the equivalent model of $[\pm\theta/0/90]_{14s}$. At the result of this study, the FE analyses for composite have indicated that the optimized ply orientation $75^{\circ}$ is and real model must use in FE analysis for accurate results.

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