Aeroelastic flutter analysis for 2D Kirchhoff and Mindlin panels with different boundary conditions in supersonic airflow

Li, Fengming; Song, Zhiguang

doi:10.1007/s00707-014-1141-1

Cited by 40 publications

(8 citation statements)

References 29 publications

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“…8 > > > > > > > > > < > > > > > > > > > : 9 > > > > > > > > > = > > > > > > > > > ; dz (16) and following definitions are considered for inertia of the panel…”

Section: Governing Equationsmentioning

confidence: 99%

“…One of the most challenges in high-speed aircrafts and missiles is an unstable flow-induced vibration known as flutter or aeroelastic instability which can be seen in subsonic, 10-14 supersonic [15][16][17][18][19] or hypersonic [20][21][22][23] flights. In aerospace engineering, it is a necessity to have a fair prediction for the critical velocity for each part of high-speed aircrafts and missiles.…”

Section: Introductionmentioning

confidence: 99%

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Flutter prediction of cylindrical sandwich panels with saturated porous core under supersonic yawed flow

Akbari

Azadi

Fahham

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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Supersonic flutter characteristics of cylindrical sandwich panels made of a saturated functionally graded porous (FGP) core and two homogeneous face sheets are studied in this paper based on the Biot’s poroelasticity theory. The third-order shear deformation theory (TSDT) is used to model the panel and the piston theory is hired to estimate the aerodynamic pressure create by the supersonic fluid flow. First, the set of the governing equations are solved numerically via generalized differential quadrature method (GDQM) and natural frequencies are calculated for various boundary conditions. Then, convergence of the solution is confirmed and its accuracy is demonstrated by comparing the results with those reported by other authors. Finally, the effects of geometrical parameters of the panel, thickness of the porous core, porosity distribution pattern, porosity parameter (size of pores), compressibility of pore fluid and yaw angle (fluid flow direction) on the flutter boundaries of FGP sandwich panels are investigated.

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“…8 > > > > > > > > > < > > > > > > > > > : 9 > > > > > > > > > = > > > > > > > > > ; dz (16) and following definitions are considered for inertia of the panel…”

Section: Governing Equationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Flutter prediction of cylindrical sandwich panels with saturated porous core under supersonic yawed flow

Akbari

Azadi

Fahham

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…The use of the first-order transverse shear deformation theory changes the form of differential operators L 1 , L 2 but not their order-see e.g., Li, Song [16].…”

Section: Brief Description Of the Flutter Problemmentioning

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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“…In order to study the 2D panel flutter with elastic boundary conditions, a new method was proposed by Li and Song. 37 Moreover, the continued application of panel flutter on flow control has been highlighted by recent studies. 38 When the fluid-structure dynamic response of panel becomes unstable and starts to flutter, the panel structural response is under limit cycle oscillation.…”

Section: Introductionmentioning

confidence: 99%

Analysis on location of maximum vibration amplitude in panel flutter

Meng

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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When the panel is under limit cycle oscillation, the location of maximum vibration amplitude always locates at 0.75 of panel length under different dynamic pressure. However, this conclusion is drawn from engineer practice without further investigations on its theoretical basis. Thus, the current study focuses on the theoretical and mathematical basis of this problem. The pattern of the location of maximum amplitude is verified at first by using three numerical methods. Then, based on the law of energy conservation, the displacement function of linear panel oscillation is derived for theoretical investigation. The linear panel consists of two structural modes. Theoretical analysis shows that, under critical dynamic pressure, the generalized displacement responses of two structural modes have opposite phase, the same vibration amplitude and the same vibration frequency. As a result, the superposition of displacement function of two structural modes, which is the displacement function of panel, leads to the occurrence of maximum vibration amplitude at 0.7 of panel length. With more structural modes considered, the location of maximum moves to 0.75 of panel length.

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Aeroelastic flutter analysis for 2D Kirchhoff and Mindlin panels with different boundary conditions in supersonic airflow

Cited by 40 publications

References 29 publications

Flutter prediction of cylindrical sandwich panels with saturated porous core under supersonic yawed flow

Flutter prediction of cylindrical sandwich panels with saturated porous core under supersonic yawed flow

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

Analysis on location of maximum vibration amplitude in panel flutter

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