Postbuckling Optimization of Laminated Composite Rectangular Plates and Stiffened Panel under Compression using Firefly Algorithm

Koide, Rubem Matimoto; Luersen, Marco Antônio; Ferreira, Ana Paula Carvalho da Silva; Lima, Leticia Mendes de

doi:10.26678/abcm.cobem2017.cob17-0623

Cited by 1 publication

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“…If we make a sum of (21) for all k and keep in mind (10) The relation (24) is a linear combination of the optimality conditions (21) or (22) and, hence, also it is the optimality condition uniting the ones for every layer. The first item in (24), if considered separately as equal to zero, means that the nonlinear mid-plane strain tensor is co-axial with the stress flow tensor (or, for 2 1    , the shear flow in the principal strain axes is equal to zero).…”

Section: Point-wise Optimality Conditionsmentioning

confidence: 99%

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Lay-Up Optimality Conditions for Stiffness Maximization of Anisotropic Composite Plates in Postbuckling

Selyugin¹

2019

Preprint

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The present paper deals with the optimization of post-buckled composite plates. The plates have a symmetric lay-up. The layer orientation angles vary in the point-wise or in the platewise ways. The von Karman theory is employed. The boundary conditions are the simple support ones or the clamped ones. The structural potential energy is treated as a measure of structural stiffness. For the plate stiffness maximization problem, the first-order necessary conditions of the local optimality are derived. The mathematical treatment of the conditions is performed. The conditions contain two terms. One of them corresponds to the mid-plane strains; another one corresponds to the plate curvatures. The optimality conditions may lead to a co-axiality of some structural tensors. An illustration of the optimality conditions is presented.-2 - INTRODUCTIONPostbuckling of thin composite plates attracts the attention of numerous researchers, working in various modern application areas. Among these applications, there are the aerospace, the automotive, the marine, and the civil ones. According to design practice in composite structures, the account of the load-carrying capability "above buckling" gives an opportunity of extra weight saving, as compared to existing traditional design.Composite plates are a part of a considerable number of structures in the above applications. The loading applied to the plates is a combination of compression and shear. The compression dominates for the structures similar to the upper panels of an airplane wing structure. As the examples of known structures designed for pure shear, one may indicate airplane wing ribs and spars, as well as some fuselage panels. As a rule, the shear-loaded plates have the so-called angle-ply symmetric lay-up. For example, buckling is not allowed in airplane structures in the case of loading up to the so-called limit loads (LL) and may be allowed for the loading level between the limit loads and the so-called ultimate loads (UL).The latter loads are 1.5 times higher than the limit loads.When optimizing the composite plate, an engineer, in fact, does his best to save the structural weight, the material cost, and the production time. Due to that, the optimization problems for the composite plates attract considerable attention at the design phase. The layup optimization problem is one of them requiring a solution at the beginning of the design process. Since the last decade of the previous century, numerous papers dealt with the lay-up optimization of composite plates. The non-exhaustive list [1]-[22] contains the important publications devoted to the postbuckling analysis and optimization. The foundations of the postbuckling theory are described in [23].

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Section: Point-wise Optimality Conditionsmentioning

confidence: 99%

“…The paper [21] considers a discrete version of the firefly algorithm (DFA). The algorithm is adapted to lay-up optimization of post-buckled composite structures.…”

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confidence: 99%

Lay-Up Optimality Conditions for Stiffness Maximization of Anisotropic Composite Plates in Postbuckling

Selyugin¹

2019

Preprint

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Postbuckling Optimization of Laminated Composite Rectangular Plates and Stiffened Panel under Compression using Firefly Algorithm

Cited by 1 publication

References 4 publications

Lay-Up Optimality Conditions for Stiffness Maximization of Anisotropic Composite Plates in Postbuckling

Lay-Up Optimality Conditions for Stiffness Maximization of Anisotropic Composite Plates in Postbuckling

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