Postbuckling Analysis of Variable Stiffness Composite Plates Using a Finite Element-Based Perturbation Method

Rahman, Tanvir; IJsselmuiden, Samuel T.; Abdalla, Mostafa; Jansen, Eelco

doi:10.1142/s0219455411004324

Cited by 61 publications

(25 citation statements)

References 12 publications

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“…In the past several years, drastic improvements in the manufacturing techniques allowed variable-stiffness constructions to become a hot topic and suitable candidates for the aerostructures of the next generation. Theoretical investigations and numerical models were carried out for analyzing their buckling [19][20][21] and post-buckling [22][23][24] response, in most cases referring to thin plate theory or FSDT [25]. Refined theories have been less commonly employed: the free vibration response of variable-stiffness plates (VSP) is investigated in [26,27] using finite elements, while the authors presented a variable-kinematics, Ritz-based procedure for buckling and free-vibration analysis [28] of VSP based on Carrera's Unified Formulation (CUF) [29][30][31].…”

Section: Introductionmentioning

confidence: 99%

Thermal Buckling Behaviour of Thin and Thick Variable-Stiffness Panels

Vescovini

Dozio

2018

J. Compos. Sci.

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The possibility of designing composite panels with non-uniform stiffness properties offers a chance for achieving highly-efficient configurations. This is particularly true for buckling-prone structures, whose response can be shaped through a proper distribution of the membrane and bending stiffnesses. The thermal buckling behaviour of composite panels is among the aspects that could largely benefit from the adoption of a variable-stiffness design, but, in spite of that, it has rarely been addressed. The paper illustrates a semi-analytical approach for evaluating the thermal buckling response of variable-stiffness plates (VSP) by considering different boundary conditions. The formulation relies upon the method of Ritz and a variable-kinematic approach, leading to a computationally efficient implementation, which is particularly useful for exploring the larger design spaces, typical of variable-stiffness configurations. Due to the possibility of choosing the underlying kinematic approach as an input of the analysis, the formulation is not restricted to thin plates, but is suitable for analyzing the response of thick plates as well. Novel results are derived, which can be useful for benchmarking purposes and for gathering insight into the mechanical behaviour of variable-stiffness plates. Furthermore, the importance of transverse shear flexibility is illustrated with respect to the boundary conditions as well as the degree of steering of the fibers.

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Section: Introductionmentioning

confidence: 99%

Thermal Buckling Behaviour of Thin and Thick Variable-Stiffness Panels

Vescovini

Dozio

2018

J. Compos. Sci.

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“…Previous works on variable stiffness laminates focused mainly on initial buckling and report an increase in critical buckling load by re-distribution of the prebuckling stresses Wu et al, 2012c). However, very few works (Rahman et al, 2011) have been reported on the study of postbuckling behaviour of VAT laminates, and where they exist, rely substantially on finite element modelling, which requires significant computational efforts in solving the nonlinear postbuckling problem. There remains an ongoing need for rapid design tools which allow optimisation studies and provide physical insight into the fundamental behaviour which is not always readily achievable using commercial finite element analysis (FEA).…”

Section: Introductionmentioning

confidence: 99%

Postbuckling analysis of variable angle tow composite plates

Wu¹,

Raju²,

Weaver³

2013

International Journal of Solids and Structures

104

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“…The numerical perturbation approach to postbuckling analysis should be mentioned as rather popular. For references, one may refer to [3], [8], and [15].…”

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Lay-Up Optimality Conditions for Stiffness Maximization of Anisotropic Composite Plates in Postbuckling

Selyugin¹

2019

Preprint

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The present paper deals with the optimization of post-buckled composite plates. The plates have a symmetric lay-up. The layer orientation angles vary in the point-wise or in the platewise ways. The von Karman theory is employed. The boundary conditions are the simple support ones or the clamped ones. The structural potential energy is treated as a measure of structural stiffness. For the plate stiffness maximization problem, the first-order necessary conditions of the local optimality are derived. The mathematical treatment of the conditions is performed. The conditions contain two terms. One of them corresponds to the mid-plane strains; another one corresponds to the plate curvatures. The optimality conditions may lead to a co-axiality of some structural tensors. An illustration of the optimality conditions is presented.-2 - INTRODUCTIONPostbuckling of thin composite plates attracts the attention of numerous researchers, working in various modern application areas. Among these applications, there are the aerospace, the automotive, the marine, and the civil ones. According to design practice in composite structures, the account of the load-carrying capability "above buckling" gives an opportunity of extra weight saving, as compared to existing traditional design.Composite plates are a part of a considerable number of structures in the above applications. The loading applied to the plates is a combination of compression and shear. The compression dominates for the structures similar to the upper panels of an airplane wing structure. As the examples of known structures designed for pure shear, one may indicate airplane wing ribs and spars, as well as some fuselage panels. As a rule, the shear-loaded plates have the so-called angle-ply symmetric lay-up. For example, buckling is not allowed in airplane structures in the case of loading up to the so-called limit loads (LL) and may be allowed for the loading level between the limit loads and the so-called ultimate loads (UL).The latter loads are 1.5 times higher than the limit loads.When optimizing the composite plate, an engineer, in fact, does his best to save the structural weight, the material cost, and the production time. Due to that, the optimization problems for the composite plates attract considerable attention at the design phase. The layup optimization problem is one of them requiring a solution at the beginning of the design process. Since the last decade of the previous century, numerous papers dealt with the lay-up optimization of composite plates. The non-exhaustive list [1]-[22] contains the important publications devoted to the postbuckling analysis and optimization. The foundations of the postbuckling theory are described in [23].

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Postbuckling Analysis of Variable Stiffness Composite Plates Using a Finite Element-Based Perturbation Method

Cited by 61 publications

References 12 publications

Thermal Buckling Behaviour of Thin and Thick Variable-Stiffness Panels

Thermal Buckling Behaviour of Thin and Thick Variable-Stiffness Panels

Postbuckling analysis of variable angle tow composite plates

Lay-Up Optimality Conditions for Stiffness Maximization of Anisotropic Composite Plates in Postbuckling

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