Feasible Region in General Design Space of Lamination Parameters for Laminated Composites

Diaconu, Cezar G.; Sato, Masaki; Sekine, Hideki

doi:10.2514/2.1683

Cited by 68 publications

(35 citation statements)

References 13 publications

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“…It is known (see Gürdal et al 1999 andDiaconu et al 2002) that there exist the following relationships between the out-of-plane lamination parameters:…”

Section: Lamination Parameter-based Methodsmentioning

confidence: 99%

“…This is beneficial for the design optimization of composite laminates as it reduces the number of design variables. Diaconu et al (2002) used a variational approach to determine feasible regions in the space of lamination parameters as constraints in the optimization problem. Matsuzaki and Todoroki (2007) used the fractal branch-and-bound method for the stacking sequence optimization of non-symmetric composite laminates where the inplane, out-of-plane and coupling lamination parameters were treated as design variables.…”

Section: Introductionmentioning

confidence: 99%

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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 is known (see Gürdal et al 1999 andDiaconu et al 2002) that there exist the following relationships between the out-of-plane lamination parameters:…”

Section: Lamination Parameter-based Methodsmentioning

confidence: 99%

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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“…A method for obtaining an approximate feasible region is presented in [41]. [12] developed an approach to define a feasible region for all 12 lamination parameters, which was further extended by [8]. In particular, [13] derived explicit expressions describing the feasible region for ply angles limited to {0 • , ±45 • , 90 • }.…”

Section: Related Workmentioning

confidence: 99%

“…The feasible LP region is known to be convex [8,12,23], and a closed-form expression has been defined only for a limited number of combinations of the lamination parameters [41]. Expressions for a limited set of LPs have been derived by different authors.…”

Section: Related Workmentioning

confidence: 99%

Composite stacking sequence optimization for aeroelastically tailored forward-swept wings

Bach

Jebari

Viti

et al. 2016

Struct Multidisc Optim

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A method for stacking sequence optimization and aeroelastic tailoring of forward-swept composite wings is presented. It exploits bend-twist coupling to mitigate aeroelastic divergence. The method proposed here is intended for estimating potential weight savings during the preliminary aircraft design stages. A structural beam model of the composite wingbox is derived from anisotropic shell theory and the governing aeroelastic equations are presented for a spanwise discretized forward swept wing. Optimization of the system to reduce wing mass is undertaken for sweep angles of -35 • to 0 • and Mach numbers from 0.7 to 0.9. A subset of lamination parameters (LPs) and the number of laminate plies in each pre-defined direction (restricted to {0 • ,±45 • , 90 • }) serve as design variables. A bi-level hybrid optimization approach is employed, making use of a genetic algorithm (GA) and a subsequent gradientbased optimizer. Constraints are implemented to match lift requirements and prevent aeroelastic divergence, excessive deformations, airfoil stalling and structural failure. A permutation GA is then used to match specific composite ply stacking sequences to the optimum design variables with a limited number of manufacturing constraints considered for demonstration purposes. The optimization results in positive bend-twist coupling and

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“…A more accurate boundary for the feasible region can be derived based on Bloomeld et al's work [21], in which stronger links between the lamination parameters from each design subspace are obtained by using the following algebraic identity [12],…”

Section: B New Constraintsmentioning

confidence: 99%

Framework for the Buckling Optimization of Variable-Angle Tow Composite Plates

2015

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The variable angle tow (VAT) technique allows bers to be steered curvilinearly.In doing so, it oers substantially enlarged freedom for stiness tailoring of composite laminates. Prior work has shown that VAT composite structures can have improved buckling and postbuckling load carrying capability when compared to straight ber composites. However, their structural analysis and optimal design is signicantly more computationally expensive than conventional laminates due to the exponential increase in number of variables associated with spatially varying planar ber orientations in addition to the usual stacking sequence considerations. In this work, an ecient two-level optimization framework using lamination parameters as design variables has been enhanced and generalised to the design of VAT plates. At the rst level, a computationally ecient Rayleigh-Ritz model is adopted to compute the buckling load of VAT plates and is used with a globally convergent gradient-based algorithm (GCMMA) to determine the optimal distribution of lamination parameters. As a result of this analysis, new explicit stiness matrices are found in terms of component material invariants and lamination parameters. The spatial variation of lamination parameters over the planform of VAT plates is represented in the form of B-splines.The convex hull property of B-splines ensures the point-wise feasibility of lamination parameters, and notably, ensures feasibility between control points as well as at them.

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Feasible Region in General Design Space of Lamination Parameters for Laminated Composites

Cited by 68 publications

References 13 publications

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

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

Composite stacking sequence optimization for aeroelastically tailored forward-swept wings

Framework for the Buckling Optimization of Variable-Angle Tow Composite Plates

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