Surrogate-based multi-objective optimization of a composite laminate with curvilinear fibers

A variable stiffness design can increase the structural performance of a composite plate and provides flexibility for trade-offs between structural properties. In this paper, we examine the simultaneous optimization of stiffness and buckling load of a composite laminate plate with curvilinear fiber...

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Veröffentlicht in:Composite structures Jg. 94; H. 8; S. 2306 - 2313
Hauptverfasser: Arian Nik, Mahdi, Fayazbakhsh, Kazem, Pasini, Damiano, Lessard, Larry
Format: Journal Article
Sprache:Englisch
Veröffentlicht: Elsevier Ltd 01.07.2012
Schlagworte:
Buckling
Compressing
Computational efficiency
Curvilinear fiber
Fibers
Laminate design
Laminates
Metamodeling
Optimization
Plates (structural members)
Stiffness
Variable stiffness
Curvilinear fiber
Variable stiffness
Metamodeling
Optimization
Laminate design
ISSN:0263-8223, 1879-1085
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Zusammenfassung:A variable stiffness design can increase the structural performance of a composite plate and provides flexibility for trade-offs between structural properties. In this paper, we examine the simultaneous optimization of stiffness and buckling load of a composite laminate plate with curvilinear fiber paths. The problem, which falls in the area of multi-objective optimization, is formulated and solved through a surrogate-based optimization algorithm capable of finding the set of optimum Pareto solutions. We integrate surrogate modeling into an evolutionary algorithm to reduce the high computational cost required to solve the optimization process. The results show that a curvilinear fiber path can increase both buckling load and stiffness simultaneously over the quasi-isotropic laminate. Furthermore, the optimum direction for varying the fiber angle is dependent on the loading direction and boundary conditions. The results for a plate under uniform compression with free transverse edges shows that varying the fiber orientation perpendicular to the loading direction can increase the buckling load by 116% with respect to that of a quasi-isotropic laminate.
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ISSN:0263-8223
1879-1085
DOI:10.1016/j.compstruct.2012.03.021