Optimum Design of Laminated Composite Plates Using Lamination Parameters

Miki, Mitsunori; Sugiyama, Yoshihiko

doi:10.2514/3.49033

Cited by 138 publications

(62 citation statements)

References 2 publications

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“…tens of thousand) of hyperplane constraints describing the convex hull geometry. In contrasts to numerical approaches, the analytical derivation of feasibility constraints leads to a compact description of the lamination parameters space boundaries [17,7]. The 22 non-linear constraints summarised in Eq.…”

Section: Lamination Parameters Feasible Spacementioning

confidence: 99%

Optimisation of composite structures – Enforcing the feasibility of lamination parameter constraints with computationally-efficient maps

Macquart

Maes

Bordogna

et al. 2018

Composite Structures

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. Full terms of use are available: http://www.bristol.ac.uk/pure/about/ebr-terms This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting proof before it is published in its final form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. Optimisation of Composite Structures -Enforcing the Feasibility of Lamination Parameter constraints with Computationally-efficient Maps AbstractComposite materials are increasingly used in high performance structural applications because of their high strength and stiffness to weight ratios together with their significant tailoring capabilities. The stiffness of a monolithic laminate can be expressed as a linear combination of material invariants, one thickness variable, and twelve lamination parameters, which is an efficient alternative to using fibre angles as design variables. However, feasibility constraints originating from the interdependency between lamination parameters must be satisfied to obtain laminates with realistic stiffness properties. Currently, enforcing these feasibility constraints is a computationally intensive task. In this paper we propose to use normalised design variables that inherently map (i.e. correspond) to feasible lamination parameters, effectively removing the need to evaluate feasibility constraints altogether. To this end, linear and B-spline maps of the feasible lamination parameter subspace are proposed and evaluated. Results of 2D and 4D benchmark analyses and optimisation studies suggest that the proposed methodology does successfully provide an efficient means of achieving feasible results at lower computational costs.

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Section: Lamination Parameters Feasible Spacementioning

confidence: 99%

Optimisation of composite structures – Enforcing the feasibility of lamination parameter constraints with computationally-efficient maps

Macquart

Maes

Bordogna

et al. 2018

Composite Structures

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“…Since the lamination parameters are defined in terms of trigonometric functions in (14), they are bounded by constraints (Fukunaga and Sekine 1992;Miki and Sugiyama 1993). In order to find a physically meaningful combination of in-plane lamination parameters, the following requirements (Setoodeh et al 2005) are used as constraints:…”

Section: Optimisation Formulationmentioning

confidence: 99%

“…For this optimisation, the material properties are modelled using lamination parameters (Tsai and Pagano 1968), similar to previous work by Fukunaga and Vanderplaats (1991), Fukunaga and Sekine (1992), Miki and Sugiyama (1993), Abrate (1994), where lamination parameters are applied to model and optimise composite plates and shells, or wing structures in Liu and Haftka (2004). In Abdalla et al (2007) and Kameyama and Fukunaga (2007), the lamination parameters are applied for aeroelastic tailoring of composite wing structures, and in Gürdal and Olmedo (1993) and Setoodeh et al (2006), they are used to model variable stiffness composite plates.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic tailoring using lamination parameters

Thuwis

Breuker

Abdalla

et al. 2009

Struct Multidisc Optim

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The aim of the present work is to passively reduce the induced drag of the rear wing of a Formula One car at high velocity through aeroelastic tailoring. The angle-ofattack of the rear wing is fixed and is determined by the required downforce needed to get around a turn. As a result, at higher velocity, the amount of downforce and related induced drag increases. The maximum speed on a straight part is thus reduced due to the increase in induced drag. A fibre reinforced composite torsion box with extension-shear coupled upper and lower skins is used leading to bendingtorsion coupling. Three-dimensional static aeroelastic analysis is performed loosely coupling the Finite Element code Nastran and the Computational Fluid Dynamics panel code VSAERO using ModelCenter. A wing representative of Formula One rear wings is optimised for minimum induced drag using a response surface methodology. Results indicate that a substantial induced drag reduction is achievable while maintaining the desired downforce during low speed turns.

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“…The feasible region in lamination parameter space is know to be convex, 18 which is well suited for efficient gradient based optimisers. While the feasible space for membrane or bending only cases can be given analytically, 19 currently no closed form solution for the combined feasible domain is known. Therefore it is typically approximated by a set of linear constraints obtained through successive convex hull approximations.…”

Section: -7mentioning

confidence: 99%

Design of anisotropic composite shells using an isogeometric approach

Nagy¹,

Abdalla²,

Gürdal³

2010

13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference

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Thin-walled composite structures, typically modeled as Cosserat continua during the design phase, are of particular importance in aerospace and automotive applications. At the dawn of industrial scale adoption of advanced fibre placement technology, it became viable to better exploit the directional properties of composite materials. In the recent past, numerous researches were devoted to the design of shells with optimal anisotropy. In the present work, combined stiffness tailoring and shape optimal design is proposed that is naturally facilitated in a non-uniform rational B-spline based isogeometric approach. Spatial variation of stiffness properties is parameterised by means of lamination parameters and the thickness of the shell. Shape changes are easily achieved by modifying selected control point co-ordinates and weights. The method of successive approximations has been employed to solve the optimisation problem. The formulation is separable in terms of sizing variables, however, separability of the shape design problem is not enforced. The design framework is verified through selected compliance minimisation problems.

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Optimum Design of Laminated Composite Plates Using Lamination Parameters

Cited by 138 publications

References 2 publications

Optimisation of composite structures – Enforcing the feasibility of lamination parameter constraints with computationally-efficient maps

Optimisation of composite structures – Enforcing the feasibility of lamination parameter constraints with computationally-efficient maps

Aeroelastic tailoring using lamination parameters

Design of anisotropic composite shells using an isogeometric approach

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