Buckling of orthotropic plates with free and rotationally restrained unloaded edges

Bank, Lawrence C.; Yin, Jiansheng

doi:10.1016/0263-8231(95)00036-4

Cited by 80 publications

(24 citation statements)

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“…An encompassing overview is beyond the scope of the present work and the interested reader is referred to some of the standard works in this field (see e.g., [1,7,[14][15][16][17]19]) and the references cited therein. The special situation of the local buckling of structural subelements of thin-walled composite beams has also been given some attention, see e.g., the works of Brunelle and Oyibo [5], Webber et al [20], Baharlou and Leissa [2], Barbero and Raftoyiannis [4], Bank and Yin [3], Zureick and Shih [21], Qiao et al [10], Kollár [8,9], Qiao and Zuo [11,12], or Qiao and Shan [13], among others.…”

Section: T-section I-sectionmentioning

confidence: 97%

“…2. While it is well known that in the case of symmetric and purely orthotropic plates under simple loading conditions with elastic edge restraints the buckling problem can be solved in an implicit manner by solving the resultant exact transcendental equations [3,10,14,20], this procedure is not possible and alternative means of analysis must be found. For this reason, we will employ the Ritz-method wherein we will formulate especially suited displacement shape functions for the flanges.…”

Section: T-section I-sectionmentioning

confidence: 99%

“…The method is validated by comparison with accompanying finite element computations in Sect. 3 and new results concerning the local buckling behaviour of thin-walled composite beams are discussed. This paper closes with a summary and some conclusions.…”

Section: T-section I-sectionmentioning

confidence: 99%

“…The quantity ν 12 is Poisson's ratio of the layer material. In the course of the finite element modeling, the boundary conditions for all considered cross-sections at the flange edges at x 1 = 0 and at x 1 = a were formulated as u 3 0 and u 3 (x 1 = a, x 2 , x 3 = h) = 0, while for the web edges at x 1 = 0 and at x 1 = a the constraints u 2 (x 1 = 0, x 2 = b, x 3 ) = 0 and u 2 (x 1 = a, x 2 = b, x 3 ) = 0 were applied. Presently, the restraint stiffness values k were estimated employing the explicit formulae given by Qiao and Shan [13] for the discrete plate analysis of thin-walled composite cross-sections.…”

Section: Closed-form Analytical Approach For Orthotropic Layupsmentioning

confidence: 99%

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Local buckling of wide-flange thin-walled anisotropic composite beams

Mittelstedt

2007

Arch Appl Mech

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The present contribution deals with the onset of local buckling of compressively loaded thin-walled beams with open I, C, Z, T and L-cross-sections made of laminated composite materials. The method employs a discrete plate analysis approach in the course of which each structural subelement of interest-which presently is the flange-of the thin-walled cross-section is considered as a separate composite plate with elastic rotational restraints at those edges where an adjacent substructural element is located. While in many investigations the lamination schemes of webs and flanges are considered to be purely orthotropic, in the present paper the laminate layups are allowed to be of an arbitrary non-orthotropic nature, which also allows for the analysis of laminates with inherent bending-torsion coupling. The analysis of the buckling loads of the flanges of thinwalled composite beams is performed using the Ritz-method for which some especially adjusted displacement shape functions are employed. For the case of pure orthotropy, a novel closed-form solution is described. The accuracy of the employed approaches is established by comparison with accompanying finite element simulations of thin-walled composite beams. It is revealed that the presented methodology is highly efficient in terms of computational effort and yet performs with satisfying accuracy, which makes it very attractive for actual practical applications whenever the local stability behaviour of wide-flange thin-walled composite beams is to be considered.Keywords Buckling · Composites · Laminates · Thin-walled anisotropic beams · Flanges 1 Introduction Motivation and scope of the present workIn the framework of e.g., aerospace engineering, thin-walled beams are important structural elements wherein the structural subelements which form the cross-section-i.e., the webs and flanges-in many application cases are made of laminated composite materials. Common examples for open cross-sections (meaning crosssections which exhibit free edges) are I, C, Z, T and L-profiles as depicted in Fig. 1. Naturally, one of the main factors driving the design and analysis process of such thin-walled beam structures is the stability behaviour. If the length of a beam is sufficiently high, it can be assumed that rather global buckling modes in the form of Euler buckling or torsional-flexural buckling occur. However, depending on the geometry and the applied loadings, beams with thin-walled cross-sections very often also suffer from local buckling problems such as the buckling of the flanges for which adequate means of analysis have to be found. One very common concept is the so-called discrete plate analysis. In the course of this methodology, the structural subelement of interest is cut from the cross-section. At the resultant edges, rotational restraints are considered which are characterized C. Mittelstedt (B)

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Section: T-section I-sectionmentioning

confidence: 97%

Section: T-section I-sectionmentioning

confidence: 99%

Section: T-section I-sectionmentioning

confidence: 99%

Section: Closed-form Analytical Approach For Orthotropic Layupsmentioning

confidence: 99%

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Local buckling of wide-flange thin-walled anisotropic composite beams

Mittelstedt

2007

Arch Appl Mech

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“…3 concerns the situation where L ¼ a; the two shorter sides are Simply Supported (SS) and one of the longer sides is free. The other longer side corresponds to the connection between the flange and web and, therefore, possesses a rotational stiffness [24]. When calculating s cr;iso;L by Eq.…”

Section: Theory Of Elasticitymentioning

confidence: 99%

Determination of critical load for flange buckling in concentrically loaded pultruded columns

Mottram

2004

Composites Part B: Engineering

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FRP Structural Profiles and Shapes

Pecce

Cosenza

2012

Wiley Encyclopedia of Composites

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The pultrusion process allows the manufacture of profiles and shapes characterized by interesting properties that compete with those of traditional materials, such as lightness and durability. The material obtained is anisotropic and quite elastic up to failure. The mechanical properties present a high ratio of strength to elastic modulus, making deformability and buckling meaningful aspects of the structural behavior. Here, the various features are introduced, with many references to the current literature. The importance of the high shear deformability of a material on the element deformability is explained trough an experimental example. The most common failure mode of pultruded profiles is buckling, which can be global or local according the slenderness of the element and the subcomponents of the section (flange and web); also, the interaction between the two types of buckling can be taken into account by a well‐known approach based on a single relation between the element slenderness and the buckling load. Further, the design approaches and guidelines are discussed, underlining the fact that it is necessary to extend the design factors usually suggested by manufacturers so as to have reliable values for a general approach. Some information about systems for bridge decks are presented that can have various shapes of the transverse section. Finally, applications are briefly described.

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Buckling of orthotropic plates with free and rotationally restrained unloaded edges

Cited by 80 publications

References 4 publications

Local buckling of wide-flange thin-walled anisotropic composite beams

Local buckling of wide-flange thin-walled anisotropic composite beams

Determination of critical load for flange buckling in concentrically loaded pultruded columns

FRP Structural Profiles and Shapes

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