Flutter analysis of thin cracked panels using the finite element method

Chen, Wen‐Hwa; Lin, Heng-Chih

doi:10.2514/3.8986

Cited by 24 publications

(2 citation statements)

References 17 publications

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“…While some work has been done on the free vibration of a cracked composite beam, relatively less research attention has been paid to the latter issue. The flutter response of a thin cracked panel made of isotropic materials was investigated numerically by Chen and Lin [2]. A hybrid crack element is constructed to simulate the stress singularity near the crack location.…”

Section: Introductionmentioning

confidence: 99%

Crack-induced Changes in Divergence and Flutter of Cantilevered Composite Panels

Wang

Inman

Farrar

2005

Structural Health Monitoring

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The aeroelastic characteristics of a cantilevered composite panel of large aspect ratio and with an edge crack are investigated. The panel consists of several fiber-reinforced composite plies, and is modeled with a one-dimensional beam vibrating in coupled bending and torsion. The fundamental mode shapes of the cracked cantilever are used to study the interaction between a crack and aerodynamic characteristics by employing Galerkin’s method. Variation of the divergence/flutter speed with respect to the crack ratio, its location as well as the fiber angle is investigated. The divergence/flutter speed is more sensitive to the bending-torsion coupling parameter than to the presence of the crack. The crack may or may not reduce the divergence/flutter speed, depending on the fiber orientation. The qualitative analysis may help the development of an online prognosis tool for an aircraft with large aspect-ratio unswept composite wings.

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Section: Introductionmentioning

confidence: 99%

Crack-induced Changes in Divergence and Flutter of Cantilevered Composite Panels

Wang

Inman

Farrar

2005

Structural Health Monitoring

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“…It can be seen from the available literature that the work on flutter characteristics of FGM plates with cracks, to the author's knowledge is not available in the literature. Earlier studies on flutter characteristics of cracked isotropic and composite panels employed finite element procedure [Chen and Lin, 1985, Pidaparti and Chang, 1998, Shiau, 1992, Strganac and Kim, 1996. Although these numerical studies give insight into understanding the flutter behaviour, the method requires the mesh to conform to the geometry.…”

Section: Introductionmentioning

confidence: 99%

Supersonic flutter analysis of thin cracked functionally graded material plates

Natarajan,

Ganapathi,

Bordas

2012

Preprint

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In this paper, the flutter behaviour of simply supported square functionally graded material plates immersed in a supersonic flow is studied. An enriched 4-noded quadrilateral element based on field consistency approach is used for this study and the crack is modelled independent of the underlying mesh. The material properties are assumed to be temperature dependent and graded only in the thickness direction. The effective material properties are estimated using the rule of mixtures. The formulation is based on the first order shear deformation theory and the shear correction factors are evaluated employing the energy equivalence principle. The influence of the crack length, the crack orientation, the flow angle and the gradient index on the aerodynamic pressure and the frequency are numerically studied. The results obtained here reveal that the critical frequency and the critical pressure decreases with increase in crack length and it is minimum when the crack is aligned to the flow angle.

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Formulation of a super-element for the dynamic problem of a cracked plate

Lin

et al. 1998

Commun. Numer. Meth. Engng.

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On the formulation of a super-element for the dynamic problem of a cracked plate, a geometric series of similar elements is designed. This group of elements is generated layer by layer, approaching in®nitely small size around the point of singularity. The relations between similar elements for the stiness matrix and the mass matrix are established. The concept of matrix condensation is applied to formulate the superelement by using these relationships. This method presents a feasible approach to the solution of the cracked problem with an arbitrary order of stress singularity. The method is computationally economical.

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Flutter analysis of thin cracked panels using the finite element method

Cited by 24 publications

References 17 publications

Crack-induced Changes in Divergence and Flutter of Cantilevered Composite Panels

Crack-induced Changes in Divergence and Flutter of Cantilevered Composite Panels

Supersonic flutter analysis of thin cracked functionally graded material plates

Formulation of a super-element for the dynamic problem of a cracked plate

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