Finite Element Analysis of Aeroelasticity of Plates and Shells

Bismarck-Nasr, Maher N.

doi:10.1115/1.3119783

Cited by 81 publications

(8 citation statements)

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“…Datta and Deolasi [16] studied dynamic instability characteristics of isotropic plate subjected to partially distributed follower edge loading with damping. Herrmann [17], Komarakul and Arora [18], Bismarck [19], Langthjem and Sugiyama [20] and Bazant [21] have made extensive reviews on di erent problems involving non-conservative forces.…”

Section: Introductionmentioning

confidence: 98%

Dynamic instability characteristics of laminated composite plates subjected to partial follower edge load with damping

Kumar

Datta

Prabhakara³

2003

International Journal of Mechanical Sciences

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Section: Introductionmentioning

confidence: 98%

Dynamic instability characteristics of laminated composite plates subjected to partial follower edge load with damping

Kumar

Datta

Prabhakara³

2003

International Journal of Mechanical Sciences

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“…The numerical (finite element) study on supersonic panel flutter has received much attention in literatures. Finite element method to panel flutter analysis by Olson [271] in 1967 and then the review of existing works was presented by Bismarck-Nasr [272,273]. Many of the researchers have built their own procedures to analyze flutter problems.…”

Section: Numerical (Finite Element) Packagesmentioning

confidence: 99%

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

2019

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Aeroelastic optimization has become an indispensable component in the evaluation of divergence and flutter characteristics for plated/shell structures. The present paper intends to review the fundamental trends and dominant approaches in the optimal design of engineering constructions. A special attention is focused on the formulation of objective functions/functional and the definition of physical (material) variables, particularly in view of composite materials understood in the broader sense as not only multilayered laminates but also as sandwich structures, nanocomposites, functionally graded materials, and materials with piezoelectric actuators/sensors. Moreover, various original aspects of optimization problems of composite structures are demonstrated, discussed, and reviewed in depth.

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“…The aerodynamic pressure exerted by the gas flow on the elastic surface is calculated in the framework of quasi-static aerodynamic theory using the approximate formula [14] p a = − q ∂w ∂s…”

Section: Statement Of the Problemmentioning

confidence: 99%

Aeroelastic stability of cylindrical shells interacting with internal annular fluid flow

Бочкарев

Lekomtsev

2017

IOP Conf. Ser.: Mater. Sci. Eng.

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Abstract. This paper is devoted to the analysis of the dynamic behavior of cylindrical shells, containing an internal annular layer of ideal fluid and subject to the external supersonic gas flow. The aerodynamic pressure is calculated based on the quasi-static aerodynamic theory. The behavior of the compressible fluid is described in terms of the perturbation velocity potential. A mathematical formulation of the problem is developed based on the classical theory of shells and virtual displacement principle. A solution of the problem involves computation of complex eigenvalues of the coupled system of equations. The paper presents the results of numerical experiments, which were performed to estimate the influence of the fluid flow velocity on the value of the static pressure in the unperturbed gas flow for shells, interacting with fluid layers of different thicknesses. The numerical simulation shows that a reduction of the fluid layer thickness and increase of the fluid velocity produce a stabilizing effect by virtue of increasing the threshold of aerodynamic stability. However, an essential reduction of the layer thickness can lead, depending on the preset combinations of boundary conditions, to a considerable growth of the stability threshold or to the onset of instability.

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Finite Element Analysis of Aeroelasticity of Plates and Shells

Abstract: A review of the finite element method applied to the problem of supersonic aeroelastic stability of plates and shells is presented. The review is limited to linear models. Some new contributions in the field are presented and future trends are discussed.

Cited by 81 publications

References 0 publications

Dynamic instability characteristics of laminated composite plates subjected to partial follower edge load with damping

Dynamic instability characteristics of laminated composite plates subjected to partial follower edge load with damping

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

Aeroelastic stability of cylindrical shells interacting with internal annular fluid flow

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