Finite element flutter analysis of composite skew panels

Chowdary, T.V.R.; Sinha, Prabhat Kumar; Parthan, S.

doi:10.1016/0045-7949(95)00153-8

Cited by 33 publications

(16 citation statements)

References 15 publications

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“…For this, results of the present analysis technique for simply supported panels have been compared to reported results using other solution techniques. Correlation with the results of [14] are shown to demonstrate the capability of the present technique to calculate flutter dynamic pressures accurately for skewed, composite simply supported panels.…”

Section: Test Cases and Resultsmentioning

confidence: 76%

“…The simply supported panels studied in [14] are skewed with skew angles varying from 0 to 45 degrees. A unidirectional fiber composite material is used with fiber angle varying from 0 to 90 degrees.…”

Section: Test Cases and Resultsmentioning

confidence: 99%

“…where a is the side of panel and h its thickness. Both critical and flutter dynamic pressures have been calculated and the comparison of critical dynamic pressure and critical frequency with the results of [14] are shown in Fig.1 and Fig.2. As the figures show, the correlation is good over a considerable range of skew and fiber angles, except for cases in which skew angles and fiber angles are simultaneously large.…”

Section: Test Cases and Resultsmentioning

confidence: 99%

“…Most of the studies, however, are confined to rectangular panels. Solution techniques and results for quadrilateral and trapezoidal panels have been discussed in only a small number of articles, [12], [13] and [14].…”

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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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: Test Cases and Resultsmentioning

confidence: 76%

Section: Test Cases and Resultsmentioning

confidence: 99%

Section: Test Cases and Resultsmentioning

confidence: 99%

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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“…To increase the flutter speed, designers strive to increase the difference between modal frequencies by increasing the stiffness and changing the mass distribution (Wright and Cooper [14]). Flutter can also be prevented by eliminating some modes of vibration that cause the phenomenon, through the manipulation of certain design parameters (Chowdary et al [15]) or through the use of control surfaces and actuators (Foster and Yang [16]).…”

Section: Introductionmentioning

confidence: 99%

Natural Frequencies of Rectangular Laminated Plates—Introduction to Optimal Design in Aeroelastic Problems

Muc

2018

Aerospace

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Free vibration (or eigenvalue analysis) is a prerequisite for aeroelastic analysis. For divergence analysis, slope influence coefficients (rotation at point i due to unit load at point j) are calculated using free vibration mode shapes and corresponding frequencies. The lowest eigenvalue is of interest and gives the divergence speed. The present paper considers the maximization problem of eigenfrequencies for composite panels. The influence of boundary conditions and constant or variable stiffnesses on optimization results are investigated herein. A new convenient set of design variables is employed in the analysis. The computations are carried out with the use of the Rayleigh–Ritz method and Finite Element analysis (2D quadrilateral and 3D solid elements).

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