Theory of anisotropic thin-walled closed-cross-section beams

Berdichevsky, Victor L.; Armanios, Erian A.; Badir, Ashraf

doi:10.1016/0961-9526(92)90035-5

Cited by 188 publications

(107 citation statements)

References 9 publications

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“…Its derivation exploits the aerodynamics in the Laplace domain and can be found in [57]. The basic assumption of the g-method is based on the following approximation of the generalized aerodynamic matrix: (23) where g = γk and γ is the transient decay rate coefficient.…”

Section: Generalized Matrices and G-methodsmentioning

confidence: 99%

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Advanced 1D Structural Models for Flutter Analysis of Lifting Surfaces

Petrolo¹

2012

International Journal of Aeronautical and Space Sciences

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An advanced aeroelastic formulation for flutter analyses is presented in this paper. Refined 1D structural models were coupled with the doublet lattice method, and the g-method was used for flutter analyses. Structural models were developed in the framework of the Carrera Unified Formulation (CUF). Higher-order 1D structural models were obtained by using Taylor-like expansions of the cross-section displacement field of the structure. The order (N) of the expansion was considered as a free parameter since it can be arbitrarily chosen as an input of the analysis. Convergence studies on the order of the structural model can be straightforwardly conducted in order to establish the proper 1D structural model for a given problem. Flutter analyses were conducted on several wing configurations and the results were compared to those from literature. Results show the enhanced capabilities of CUF 1D in dealing with the flutter analysis of typical wing structures with high accuracy and low computational costs.

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Section: Generalized Matrices and G-methodsmentioning

confidence: 99%

“…Asymptotic-type expansions have been proposed in [23] on the basis of variational methods. That work represented the starting point of an alternative approach to constructing refined beam theories where a characteristic parameter (e.g.…”

Section: Introductionmentioning

confidence: 99%

Advanced 1D Structural Models for Flutter Analysis of Lifting Surfaces

Petrolo¹

2012

International Journal of Aeronautical and Space Sciences

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“…For thin-walled single-cell composite beams, the work of Ref. 16 is a good alternative. Both are used in this work.…”

Section: Static Aeroelastic Tailoringmentioning

confidence: 99%

“…First, using recently developed tools 14,15,16 it is now possible to rigorously collapse a three-dimensional (3-D) built-up structural model to either one-(1-D) or two-dimensional (2-D) models. Since at least the trends of all phenomena known to be significant in wings of moderate to high aspect ratio can be represented in terms of 1-D models (i.e., refined beam theory), the geometrically-exact intrinsic beam theory is used, along with the corresponding asymptotically correct cross-sectional analysis.…”

Section: Present Approachmentioning

confidence: 99%

Aeroelastic analysis of composite wings

Cesnik

Hodges

Patil

1996

37th Structure, Structural Dynamics and Materials Conference

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An aeroelastic stability analysis is presented for high-aspect ratio composite wings. The structural model is based on an asymptotically correct crosssectional formulation and a nonlinear geometric exact beam analysis, both derivable from 3-D elasticity. A new 2-D unsteady inflow finite-state theory is considered for the aerodynamic part of the solution. Theodorsen theory is also implemented and used for most of the preliminary tests. The paper discusses, among other things, the importance of using the right stiffness formulation in order to model material couplings, the variations of divergence and flutter speeds with the changes in the lamination angle of a box-beam model of a wing cross section, and some of the effects of a nonlinear structural model on the aeroelastic stability of a slender wing.

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“…Generalized beam theories (GBT) originated with Schardt's work [22] and improved classical theories, by using a piecewise beam description of thin-walled sections [23]. An asymptotic type expansion, in conjunction with variational methods, was proposed by Berdichevsky et al [24], where a commendable review of prior works on beam theory development was given. An alternative approach to formulating refined beam theories, based on asymptotic variational methods (VABS), has led to an extensive contribution in the last few years [25].…”

Section: Introductionmentioning

confidence: 99%

Static Aeroelastic Response of Wing-Structures Accounting for In-Plane Cross-Section Deformation

Varello¹,

Lamberti²,

Carrera³

2013

International Journal of Aeronautical and Space Sciences

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In this paper, the aeroelastic static response of flexible wings with arbitrary cross-section geometry via a coupled CUF-XFLR5 approach is presented. Refined structural one-dimensional (1D) models, with a variable order of expansion for the displacement field, are developed on the basis of the Carrera Unified Formulation (CUF), taking into account cross-sectional deformability. A three-dimensional (3D) Panel Method is employed for the aerodynamic analysis, providing more accuracy with respect to the Vortex Lattice Method (VLM). A straight wing with an airfoil cross-section is modeled as a clamped beam, by means of the finite element method (FEM). Numerical results present the variation of wing aerodynamic parameters, and the equilibrium aeroelastic response is evaluated in terms of displacements and in-plane cross-section deformation. Aeroelastic coupled analyses are based on an iterative procedure, as well as a linear coupling approach for different free stream velocities. A convergent trend of displacements and aerodynamic coefficients is achieved as the structural model accuracy increases. Comparisons with 3D finite element solutions prove that an accurate description of the in-plane crosssection deformation is provided by the proposed 1D CUF model, through a significant reduction in computational cost.

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Theory of anisotropic thin-walled closed-cross-section beams

Cited by 188 publications

References 9 publications

Advanced 1D Structural Models for Flutter Analysis of Lifting Surfaces

Advanced 1D Structural Models for Flutter Analysis of Lifting Surfaces

Aeroelastic analysis of composite wings

Static Aeroelastic Response of Wing-Structures Accounting for In-Plane Cross-Section Deformation

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