On Laminate Configurations for Simultaneous Failure

Fukunaga, H.; Chou, Tsu-Wei

doi:10.1177/002199838802200305

Cited by 32 publications

(10 citation statements)

References 5 publications

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“…These can be either continuous or discrete. Besides other types of design variables were used like lamination parameters, 56,77,109,110,125,142,154,158,219,228–230,245–247,263,264,270,278,302,359,446,462,493,521,531,559,572,573,614,645,646,663,672,678,679,691,699,708,729,757,794,796,810,814,836,837,840,849,851,867,868,896–898,930–932,948,957,962,1001,1002 material of the layers, 64,…”

Section: Introductionmentioning

confidence: 99%

Optimum Design of Composite Structures: A Literature Survey (1969–2009)

Sonmez

2016

Journal of Reinforced Plastics and Composites

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Optimum structural design of composites is a research subject that has drawn the attention of many researchers for more than 40 years with a growing interest. In this study, a review of the literature on this subject is presented. The papers are classified according to the type of the composite structure optimized in those studies, the loading conditions, the objective function, the structural analysis method, the design variables, the constraints, the failure criteria, and the search algorithm used by the researchers.

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Section: Introductionmentioning

confidence: 99%

Optimum Design of Composite Structures: A Literature Survey (1969–2009)

Sonmez

2016

Journal of Reinforced Plastics and Composites

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“…The use of lamination parameters to represent the in-plane and flexural stiffness in the optimization of laminated composites was first used by Tsai et al (1968) and later applied to the buckling optimization of orthotropic laminated plates by Fukunaga and Hirano (1982). Miki (1982), Fukunaga and Chou (1988), and Fukunaga and Sekine (1993) also used lamination parameters for tailoring mechanical properties of laminated composites. In a composite optimization problem, lamination parameters can be used as design variables instead of the layer thicknesses and ply angles since each element of the stiffness matrix of laminated composites can be expressed as a linear function of lamination parameters.…”

Section: Introductionmentioning

confidence: 99%

Weight and mechanical performance optimization of blended composite wing panels using lamination parameters

Liu

Торопов

Barton

et al. 2015

Struct Multidisc Optim

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In this paper, a lamination parameter-based approach to weight optimization of composite aircraft wing structures is addressed. It is a bi-level procedure where at the top level lamination parameters and numbers of plies of the pre-defined angles (0, 90, 45 and −45°) are used as design variables, the material volume is treated as an objective function to be minimized subject to the buckling, strength and ply percentage constraints. At the bottom level the optimum stacking sequence is obtained subject to the requirements on blending and preservation of mechanical properties. To ensure composite blending, a multi-stage optimization is performed by a permutation genetic algorithm aiming at matching the lamination parameters passed from the top level optimization as well as satisfying the layup rules. Two new additional criteria, the 90°ply angle jump index and the stack homogeneity index, are introduced to control the uniformity of the three ply angles (0, 90, 45 and −45) spread throughout the stack as well as improve the stack quality and mechanical performance by encouraging 45°angle change between neighbouring groups of plies. The results of the application of this approach are Page 2 of 28 compared to published results to demonstrate the potential of the developed technique. Keywords:Laminated composite, optimization, stacking sequence, blending, lamination parameters IntroductionStacking sequence optimization of laminated composite structures to satisfy ply continuity (blending) requirements has recently attracted considerable attention by Gürdal et al. (1999), Kristinsdottir et al. (2001), Liu and Haftka (2001), Seresta et al. (2007), Liu and Krog (2008), Liu et al. (2011). Liu et al. (2000 presented a bi-level (global and bottom) strategy for optimization of a composite wing box structure. At the global level, continuous optimization of thicknesses of 0, 90, 45 and 45°plies was performed to minimize the weight of a wing box subject to strain and buckling constraints. For a given number of plies of each orientation and in-plane loads, a permutation genetic algorithm (GA) was used at the bottom level to optimize the stacking sequence in order to maximize the buckling load. The optimum buckling load, which was treated as a function of the loading and the numbers of plies of 0, 90, 45 and 45°orientation, was evaluated by a cubic polynomial response surface approximation. This bi-level approach was also used for maximization of buckling load of composite panels by Liu et al. (2004), layup optimization of anisotropic laminated composite panels by Bloomfield et al. (2009) and stacking sequence optimization of blended composite structures by Liu et al. (2011). The use of lamination parameters to represent the in-plane and flexural stiffness in the optimization of laminated composites was first used by Tsai et al. (1968) and later applied to the buckling optimization of orthotropic laminated plates by Fukunaga and Hirano (1982). Miki (1982), Fukunaga and Chou (1988), and Fukunaga and Sekine (1993) also u...

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“…It was first used by Tsai et al [11] and later applied to the buckling optimization of orthotropic laminated plates by Fukunaga and Hirano [12]. Miki [13] and Fukunaga [14] used lamination parameters for tailoring mechanical properties of laminated composites. In a laminated composite optimization problem, lamination parameters can be used as design variables instead of layer thicknesses and ply angles in order to avoid falling into local optima.…”

Section: Introductionmentioning

confidence: 99%

Ply number rounding-off in optimization of composite structures using lamination parameters

Liu¹,

Toropov²

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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A bi-level optimization strategy for finding the optimal ply numbers and stacking sequence in composite structures has become one of the most popular techniques in recent years. When the optimization technique is based on the use of lamination parameters, the top level optimization has two subsets of design variables for each substructure (e.g., a panel in wing design): lamination parameters treated as continuous design variables, and three integers that define the number of plies of 0, 90 and ±45 degree orientation. When a continuous optimizer is used, there is a need for an algorithm to perform a rounding-off of obtained continuous representation of the number of plies to an integer value that, ideally, does not alter the mechanical performance of a panel. In this paper three schemes based on the lamination parameter matching are introduced to determine the integer values of the ply numbers. The strategy is to use a binary code controlling the ply number rounding-off in order to obtain a discrete number of plies of each orientation per composite panel. An optimization problem is formulated where the objective function (to be minimized) defines how close the lamination parameter values and the panel thickness, obtained in the top level optimization, are to their values when integer ply numbers are considered. Such an optimization problem is solved by a permutation GA for each individual panel. A wing box benchmark problem is used to demonstrate the potential of these methods.

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On Laminate Configurations for Simultaneous Failure

Cited by 32 publications

References 5 publications

Optimum Design of Composite Structures: A Literature Survey (1969–2009)

Optimum Design of Composite Structures: A Literature Survey (1969–2009)

Weight and mechanical performance optimization of blended composite wing panels using lamination parameters

Ply number rounding-off in optimization of composite structures using lamination parameters

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