A Note on the Elastic and Geometric Bounds for Composite Laminates

Vannucci, Paolo

doi:10.1007/s10659-012-9406-1

Cited by 38 publications

(48 citation statements)

References 13 publications

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“…These constraints ensure that the optimum values of the polar parameters resulting from the rst step correspond to a feasible laminate that will be designed during the second step of the optimisation strategy, see [38]. Since the laminate is quasi-homogeneous, such constraints can be written only for matrix [A * ] as follows:…”

Section: Mechanical Design Variablesmentioning

confidence: 99%

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A New Paradigm for the Optimum Design of Variable Angle Tow Laminates

Montemurro

Catapano

2016

Variational Analysis and Aerospace Engineering

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Section: Mechanical Design Variablesmentioning

confidence: 99%

“…For a wide discussion upon the laminate feasibility and geometrical bounds as well as on the importance of the quasi-homogeneity assumption the reader is addressed to [38].…”

Section: (Ij)mentioning

confidence: 99%

A New Paradigm for the Optimum Design of Variable Angle Tow Laminates

Montemurro

Catapano

2016

Variational Analysis and Aerospace Engineering

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“…These constraints ensure that the obtained optimal polar parameters correspond to a feasible laminate that will be designed during the second step of the optimisation strategy, see [28]. Since the laminate is quasi-homogeneous, such geometric constraints can be written only for tensor A * as follows:…”

Section: Mechanical Design Variablesmentioning

confidence: 99%

“…For a wide discussion upon the laminate feasibility and geometrical bounds as well as on the importance of the quasi-homogeneity assumption the reader is addressed to [28].…”

Section: Mechanical Design Variablesmentioning

confidence: 99%

A multi-scale approach for the optimum design of sandwich plates with honeycomb core. Part II: the optimisation strategy

Catapano

Montemurro

2014

Composite Structures

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is an open access repository that collects the work of Arts et Métiers ParisTech researchers and makes it freely available over the web where possible. )>IJH=?JThis work deals with the problem of the optimum design of a sandwich panel. The design strategy that we propose is a numerical optimisation procedure that does not make any simplifying assumption to obtain a true global optimum conguration of the system. To face the design of the sandwich structure at both meso and macro scales, we use a two-level optimisation strategy: at the rst level we determine the optimal geometry of the unit cell of the core together with the material and geometric parameters of the laminated skins, while at the second level we determine the optimal skins lay-up giving the geometrical and material parameters issued from the rst level. The two-level strategy relies both on the use of the polar formalism for the description of the anisotropic behaviour of the laminates and on the use of a genetic algorithm as optimisation tool to perform the solution search. To prove its eectiveness, we apply our strategy to the least-weight design of a sandwich plate, satisfying several constraints: on the rst buckling load, on the positive-deniteness of the stiness tensor of the core, on the ratio between skins and core thickness and on the admissible moduli for the laminated skins.

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“…Particularly, the objective of the present work is twofold: on one hand it aims of clarifying the physical meaning of the higher-order stiffness matrices while on the other hand it intends of estimating their influence on the elastic response of the laminate. To these purposes the polar method initially introduced by Verchery [14], later enriched and deeply investigated by Vannucci and his co-workers [15][16][17][18][19] and recently extended to the FSDT of laminates [20] is here employed (for the first time) within the framework of the TSDT. In particular, the expression of the polar parameters of the laminate higher-order stiffness matrices is analytically derived.…”

Section: Introductionmentioning

confidence: 99%

The polar analysis of the Third-order Shear Deformation Theory of laminates

Montemurro

2015

Composite Structures

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a b s t r a c tIn this paper the Verchery's polar method is extended to the conceptual framework of the Reddy's Third-order Shear Deformation Theory (TSDT) of laminates. In particular, a mathematical representation based upon tensor invariants is derived for all the laminate stiffness matrices (basic and higher-order stiffness terms). The major analytical results of the application of the polar formalism to the TSDT of laminates are the generalisation of the concept of a quasi-homogeneous laminate as well as the definition of some new classes of laminates. Moreover, it is proved that the elastic symmetries of the laminate shear stiffness matrices (basic and higher-order terms) depend upon those of their in-plane counterparts. As a consequence of these results a unified formulation for the problem of designing the laminate elastic symmetries in the context of the TSDT is proposed. The optimum solutions are found within the framework of the polar-genetic approach, since the objective function is written in terms of the laminate polar parameters, while a genetic algorithm is used as a numerical tool for the solution search. In order to support the theoretical results, and also to prove the effectiveness of the proposed approach, some new and meaningful numerical examples are discussed in the paper.

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A Note on the Elastic and Geometric Bounds for Composite Laminates

Cited by 38 publications

References 13 publications

A New Paradigm for the Optimum Design of Variable Angle Tow Laminates

A New Paradigm for the Optimum Design of Variable Angle Tow Laminates

A multi-scale approach for the optimum design of sandwich plates with honeycomb core. Part II: the optimisation strategy

The polar analysis of the Third-order Shear Deformation Theory of laminates

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