Optimum stacking sequence design of composite materials Part I: Constant stiffness design

Ghiasi, Hossein; Pasini, Damiano; Lessard, Larry

doi:10.1016/j.compstruct.2009.01.006

Cited by 283 publications

(128 citation statements)

References 114 publications

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“…Different optimization methods have been investigated for VAT laminates. A review of optimization methods for VAT and UD laminates is available in References [36] and [37], with Genetic Algorithms (GA) being one of the most popular methods. Although GAs can be computationally expensive, they can be used for problems with nonlinearities, discontinuous variables or objective functions, as gradient information is not required.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Tow-Steered Composite Wing Laminates for Aeroelastic Tailoring

et al. 2015

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Section: Introductionmentioning

confidence: 99%

Optimization of Tow-Steered Composite Wing Laminates for Aeroelastic Tailoring

et al. 2015

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“…Designing such laminates for various strength and stiffness requirements involves an integerprogramming problem for selecting the best number of plies of each orientation, and then determining an optimal stacking sequence. An extensive review of the topic can be found in recent paper by Ghiasi et al (2009Ghiasi et al ( , 2010 and the earlier paper by Venkataraman and Haftka (1999). It showed that two main scenarios are classified: constant stiffness (the stacking sequence is uniform for the entire structure) and variable stiffness (material distribution and fiber orientation might change over the structural domain).…”

Section: Introductionmentioning

confidence: 99%

Stacking sequence optimization with genetic algorithm using a two-level approximation

Chen

Lin

et al. 2013

Struct Multidisc Optim

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We propose a new method for laminate stacking sequence optimization based on a two-level approximation and genetic algorithm (GA), and establish an optimization model including continuous size variables (thicknesses of plies) and discrete variables (0/1 variables that represent the existence of each ply). To solve this problem, a first-level approximate problem is constructed using the branched multipoint approximate (BMA) function. Since mixed-variables are involved in the first-level approximate problem, a new optimization strategy is introduced. The discrete variables are optimized through the GA. When calculating the fitness of each member in the population of GA, a second-level approximate problem that can be solved by the dual method is established to obtain the optimal thicknesses corresponding to the each given ply orientation sequence. The two-level approximation genetic algorithm optimization is performed starting from a ground laminate structure, which could include relatively arbitrarily discrete set of angles. The method is first applied to cylindrical laminate design examples to demonstrate its efficiency and accuracy compared with known methods. The capacity of the optimization strategy to solve more complex problems is then demonstrated using a design example. With the presented method, the stacking sequence in analytical tools can be directly taken as design variables and no intermediate variables need be adopted.

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“…The variable thickness, ply orientation, layer shape and stacking sequence not only increase design flexibility, but also bring great challenges for structural designers [2]. Because of high-dimensional design space and complicated constraints, heuristic algorithms were adopted to attack this problem [3]. The most widely used is a genetic algorithm (GA), an 18-panel horseshoes design problem was first proposed in [4], with a commercial software DARWIN used for optimization.…”

Section: Introductionmentioning

confidence: 99%

A framework for design and optimization of tapered composite structures. Part I: From individual panel to global blending structure

Jing

Qin

Silberschmidt

2016

Composite Structures

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Additional Information:• This paper was accepted for publication in the journal Compos- b s t r a c tA novel framework to design tapered composite structures is proposed for buckling analysis with multiple manufacturing constraints, with variables dealt with separately at different levels and manufacturing constraints divided and imposed in each step. The framework is based on two techniques -a sequential permutation table (SPT) method and a global shared-layer blending (GSLB) method; a design concept is extending from an individual panel to the overall structure by improving its blending property. A problem to design an 18-panel tapered composite structure is adopted to study and validate the proposed framework; a detailed design process is executed step by step to demonstrate the improvements of blending property. Multiple manufacturing constraints are analyzed for the obtained optimal solution, which is also compared with previous studies. The high efficiency of the proposed framework implies its potential for design of large-scale composite structures with complex manufacturing constraints.

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Optimum stacking sequence design of composite materials Part I: Constant stiffness design

Cited by 283 publications

References 114 publications

Optimization of Tow-Steered Composite Wing Laminates for Aeroelastic Tailoring

Optimization of Tow-Steered Composite Wing Laminates for Aeroelastic Tailoring

Stacking sequence optimization with genetic algorithm using a two-level approximation

A framework for design and optimization of tapered composite structures. Part I: From individual panel to global blending structure

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