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논문 기본 정보
- 자료유형
- 학술대회자료
- 저자정보
- 발행연도
- 2007.5
- 수록면
- 3,520 - 3,525 (6page)
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초록· 키워드
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Motivated by needs such as those in the aerospace industry, this paper demonstrates ability to significantly increase buckling loads of perforated composite laminated plates by synergizing FEM and a genetic optimization algorithm (GA). Plate geometry is discretized into specially-developed 3D degenerated eight-node shell isoparametric layered composite elements. General shell theory, involving incremental nonlinear finite element equilibrium equation, is employed. Fiber orientation within individual plies of each element is controlled independently by the genetic algorithm. Eigen buckling analysis is performed using the subspace iteration method. Available results demonstrate the approach is superior to more conventional methodologies such as modifying ply thickness or the stacking sequence of individual rectilinear plies having common fiber orientation through the plate.
목차
Abstract
INTRODUCTION
ANALYTICAL FORMULATION OF LAMINATED COMPOSITE
EXAMPLES
RESULTS
CONCLUSIONS
ACKNOWLEDGEMENTS
REFERENCES
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UCI(KEPA) : I410-ECN-0101-2009-550-016790123