Nonlinear supersonic flutter of laminated composite plates under thermal loads

Liaw, D. G.

doi:10.1016/s0045-7949(94)00487-0

Cited by 22 publications

(12 citation statements)

References 13 publications

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“…7a. It is concluded that with slight yawing of the flow direction from the fiber orientation, the flutter behavior of [0] 4S panel changes from the first and fifth mode coupling (Mode (1,5)) to the first and second mode coupling (Mode (1,2)), which results in a considerable decrease of the flutter dynamic pressure.…”

Section: Resultsmentioning

confidence: 99%

“…Two good survey articles of panel flutter theories and tests are given by Dowell [1] and Mei et al [2]. Linear and nonlinear flutter behaviors of laminated panels are studied using the classical laminated plate theory (CLPT) by many authors [3][4][5][6][7][8][9][10]. The approximate methods, such as orthotropic theory [11] and anisotropic theory [12], are also employed in flutter analysis for laminated plates.…”

Section: Introductionmentioning

confidence: 99%

“…The effects of lay-up schedule, fiber orientation, flow direction, skew angle etc. on the flutter characteristics of laminated panels are investigated by many authors [2][3][4][5][6][7][8][9][10][11][12][13][16][17][18][19][20][21][22]. However, most of the studies are conducted for thin panels, to the authors' knowledge, the flutter analysis of thick or moderately thick laminated panels has not been reported in any major international journal.…”

Section: Introductionmentioning

confidence: 99%

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Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

Xia

2011

Acta Mech Sin

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The influence of fiber orientation, flow yaw angle and length-to-thickness ratio on flutter characteristics of angle-ply laminated plates in supersonic flow is studied by finite element approach. The structural model is established using the Reissner-Mindlin theory in which the transverse shear deformation is considered. The aerodynamic pressure is evaluated by the quasi-steady first-order piston theory. The equations of motion are formulated based on the principle of virtual work. With the harmonic motion assumption, the flutter boundary is determined by solving a series of complex eigenvalue problems. Numerical study shows that (1) The flutter dynamic pressure and the coalescence of flutter modes depend on fiber orientation, flow yaw angle and length-to-thickness ratio; (2) The laminated plate with all fibers aligned with the flow direction gives the highest flutter dynamic pressure, but a slight yawing of the flow from the fiber orientation results in a sharp decrease of the flutter dynamic pressure; (3) The angle-ply laminated plate with fiber orientation angle equal to flow yaw angle gives high flutter dynamic pressure, but not the maximum flutter dynamic pressure; (4) With the decrease of length-to-thickness ratio, an adverse effect due to mode transition on the flutter dynamic pressure is found.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

Xia

2011

Acta Mech Sin

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“…Nonlinear coupling between these effects makes snapthrough challenging to model accurately. An extensive literature exists on the subject, with models describing different degrees of geometric nonlinearity [5,6], material nonlinearity [7,8,9], thermal and acoustic loading [10,11,12], and various combinations of these factors [13,14].…”

Section: Introductionmentioning

confidence: 99%

A lower bound on snap-through instability of curved beams under thermomechanical loads

Stanciulescu

Mitchell

Chandra

et al. 2012

International Journal of Non-Linear Mechanics

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A nonlinear finite element formulation (three dimensional continuum elements) is implemented and used for modeling dynamic snap-through in beams with initial curvature. We identify a nontrivial (nonflat) configuration of the beam at a critical temperature value below which the beam will no longer experience snap-through under any magnitude of applied quasistatic loadfor beams with various curvatures. The critical temperature is shown to successfully eliminate snap-through in dynamic simulations at quasistatic loading rates. Thermomechanical coupling is included in order to model a physically minimal amount of damping in the system, and the resulting post-snap vibrations are shown to be thermoelastically damped. We propose a test to determine the critical snap-free temperature for members * Corresponding author. Tel.: +1713 348 4704; fax: +1713 348 5268. of general geometry and loading pattern; the analogy between mechanical prestress and thermal strain that holds between the static and dynamic simulations is used to suggest a simple method for reducing the vulnerability of thin-walled structural members to dynamic snap-through in members of large initial curvature via the introduction of initial pretension.

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“…The fourth type remedies both 'a' and 'b'. The aerodynamic theory employed for the most part of panel flutter at supersonic Mach numbers (M∞ > 1.4) is the quasi-steady first order piston theory introduced by Ashley and Zartarian [5] A vast amount of literature exists on panel flutter using different aerodynamic theories to model the aerodynamic pressure as well as different structure models [6][7][8][9][10][11][12][13].…”

Section: Introductionmentioning

confidence: 99%

Non-linear panel flutter for temperature-dependent functionally graded material panels

Ibrahim¹,

Tawfik

Al-Ajmi

2007

Comput Mech

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The non-linear flutter and thermal buckling of an FGM panel under the combined effect of elevated temperature conditions and aerodynamic loading is investigated using a finite element model based on the thin plate theory and von Karman strain-displacement relations to account for moderately large deflection. The aerodynamic pressure is modeled using the quasi-steady first order piston theory. The governing non-linear equations are obtained using the principal of virtual work adopting an approach based on the thermal strain being a cumulative physical quantity to account for temperature dependent material properties. This system of non-linear equations is solved by Newton-Raphson numerical technique. It is found that the temperature increase has an adverse effect on the FGM panel flutter characteristics through decreasing the critical dynamic pressure. Decreasing the volume fraction enhances flutter characteristics but this is limited by structural integrity aspect. The presence of aerodynamic flow results in postponing the buckling temperature and in suppressing the post buckling deflection while the temperature increase gives way for higher limit cycle amplitude.

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Nonlinear supersonic flutter of laminated composite plates under thermal loads

Cited by 22 publications

References 13 publications

Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

A lower bound on snap-through instability of curved beams under thermomechanical loads

Non-linear panel flutter for temperature-dependent functionally graded material panels

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