Supersonic flutter analysis of clamped symmetric composite panels using shear deformable finite elements

Lee, In; Cho, Maeng-Hyo

doi:10.2514/3.10656

Cited by 12 publications

(3 citation statements)

References 4 publications

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“…Note that all of the elements of the mass matrix are linear combinations of area integral ITR(m,n) of simple polynomials over the trapezoidal panel. The mass matrix is dependent on the material density, the thickness terms rk and the panel shape variables (through U, and Vj as given by equation (11) of part one of this paper).…”

Section: Tk = T1 : I=1mentioning

confidence: 99%

“…2) Mass matrix sensitivities with respect to shape design variables The mass matrix is dependent on the shape variables through the coefficients U, and 1/1 and the area integrals IRT(m,n). Analytical sensitivities for U, and Vj are obtained through direct differentiation of equation (11) of part one of the paper. The derivatives of the area integrals with respect to x, where x is any shape variable, are to be prepared.…”

Section: Analytic Sensitivitiesmentioning

confidence: 99%

“…As an aeroelastic research problem, it includes linear and nonlinear stability and dynamic response, dynamics of systems with random parameters, [6], and interactions between static and dynamic instabilities in the presence of in-plane loads and thermal effects, [7] and [8]. Panel flutter has been used to study applications of composite materials, [9] and [10], and transverse shear effects, [11]. Most of the studies, however, are confined to rectangular panels.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

Elnomrossy

Mehanna

1999

International Conference on Aerospace Sciences and Aviation Tec

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The equivalent plate modeling formulation of composite wings, described in Part One, is extended in this paper to include the explicit analytic expressions for terms of the mass and aerodynamic matrices. Analytic sensitivities of the mass and aerodynamic matrices with respect to panel shape, thickness and fiber orientations are derived. Before proceeding in the study of analytic sensitivities using the derived expressions, the accuracy of its panel flutter analysis was numerically tested for simply supported panels of trapezoidal and skewed shape, of isotropic and composite materials and variable fiber orientations. The nondimensional critical dynamic pressure and critical frequency of flutter are compared with the results of finite element flutter analysis of composite skew panels by Chowdary, T.V.R. and al given in "Computers and Structures", (1996). The correlation of the results is good for moderate in-plane loading. Accuracy of the approximations is studied for the integration with nonlinear programming/approximation concept aeroelastic design synthesis methodology.

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Section: Tk = T1 : I=1mentioning

confidence: 99%

Section: Analytic Sensitivitiesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

Elnomrossy

Mehanna

1999

International Conference on Aerospace Sciences and Aviation Tec

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Adaptive Composite Systems: Modeling and Applications

Suleman¹

2002

Encyclopedia of Smart Materials

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In the past decade, technological developments in materials and computer sciences have evolved to the point where their synergistic combination have culminated in a new field of multidisciplinary research in adaptation. The advances in material sciences have provided a comprehensive and theoretical framework for implementing multifunctionality in materials, and the development of high speed digital computers has permitted transforming that framework into methodologies for practical design and production. The concept is elementary: a highly integrated sensor system provides data on the structural environment to a processing and control system which in turn signals integrated actuators to modify the structural properties appropriately. Multifunctional materials embedded in adaptive composite systems have presented exceptional promise in engineering design problems that require solutions in active vibration suppression, shape control, and noise attenuation. Piezoelectric materials, shape memory alloys, and magnetostrictive materials are the three most recognized types. These materials develop strains or displacements when exposed to electric, thermal, and magnetic fields, respectively.

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Shear deformation and sandwich configuration

Bert¹

1995

Buckling and Postbuckling of Composite Plates

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Supersonic flutter analysis of clamped symmetric composite panels using shear deformable finite elements

Cited by 12 publications

References 4 publications

Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

Adaptive Composite Systems: Modeling and Applications

Shear deformation and sandwich configuration

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