Panel flutter of curvilinear composite laminated plates in the presence of delamination

Fazilati, Jamshid

doi:10.1177/0021998318754641

Cited by 17 publications

(5 citation statements)

References 14 publications

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“…From above analyses, it can be found that in previous studies on the flutter characteristics of the composite laminated panels, the fibers were laid along a straight line. To further improve the aeroelastic stability of the composite laminated panels, the flutter characteristics of composite laminated panels with curvilinear fibers have recently attracted the attentions of scientists 216–218 . For example, the flutter characteristic of a cantilever composite laminated panel with curvilinear fibers in supersonic airflow was studied by Camacho et al 217 As displayed in Figure 14, the orientation of the curvilinear fibers was defined by three functions, and the influences of the fiber orientation on the flutter bounds of the composite laminated panels were analyzed.…”

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

“…For example, the flutter characteristic of a cantilever composite laminated panel with curvilinear fibers in supersonic airflow was studied by Camacho et al 217 As displayed in Figure 14, the orientation of the curvilinear fibers was defined by three functions, and the influences of the fiber orientation on the flutter bounds of the composite laminated panels were analyzed. In addition, Fazilati 218 analyzed the combined effects of curvilinear fiber orientation and delamination zone on the flutter behaviors of a rectangular composite laminated panel.…”

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

“…To further improve the aeroelastic stability of the composite laminated panels, the flutter characteristics of composite laminated panels with curvilinear fibers have recently attracted the attentions of scientists. [216][217][218] For example, the flutter characteristic of a cantilever composite laminated panel with curvilinear fibers in supersonic airflow was studied by Camacho et al 217 As displayed in Figure 14, the orientation of the curvilinear fibers was defined by three functions, and the influences of the fiber orientation on the flutter bounds of the composite laminated panels were analyzed. In addition, Fazilati 218 analyzed the combined effects of curvilinear fiber orientation and F I G U R E 13 Simplified model of (A) 2D wing/external tank system, and (B) fuel sloshing system.…”

Section: Panelsmentioning

confidence: 99%

See 2 more Smart Citations

Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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Flutter is a self-excited vibration under the interaction of the inertial force, aerodynamic force, and elastic force of the structure. After the flutter occurs, the aircraft structures will exhibit limit cycle oscillation, which will cause catastrophic accidents or fatigue damage to the structures. Therefore, it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures. This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures. The mechanism of aeroelastic flutter of wings and panels is presented. The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized. Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented. Finally, the paper ends with conclusions, which highlight challenges of the development in aeroelastic analysis and flutter control, and provide a brief outlook on the future investigations. This study aims to present a comprehensive understanding of aeroelastic analysis and flutter control. It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability.

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Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

Section: Panelsmentioning

confidence: 99%

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Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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“…Significantly large numbers of theoretical studies were devoted to the study of plates and shells in a supersonic gas flow (Dowell, 1970;Fazilati, 2018;Merrett & Hilton, 2010;Vedeneev, 2012). In these references, flutter problems were mainly solved in an elastic statement.…”

Section: Introductionmentioning

confidence: 99%

Numerical modeling of nonlinear vibrations of viscoelastic shallow shells

Khudayarov¹,

Ruzmetov²,

Turaev³

et al. 2020

10.5267/j.esm

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This paper presents a mathematical model of nonlinear supersonic flutter of viscoelastic shells. To describe the strain processes in shallow shells, the Boltzmann-Volterra integral model is used. Based on linear integral models in geometrically nonlinear formulations, equations of nonlinear oscillations of shallow shells are derived. The Koltunov-Rzhanitsyn kernel is used as a relaxation kernel. The equations of motion of shallow shells after applying the Bubnov-Galerkin method in axial coordinates are reduced to solve a system of nonlinear integro-differential equations (IDE) with variable coefficients relative to the time function. The IDE solution is found numerically using quadrature formulas.

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“…A number of studies have been reported in the literature, in which VSCL could be designed to improve buckling resistance [11], reduce stress concentrations around holes [12], maximize the fundamental natural frequency [13], and optimize aeroelastic characteristics of a composite wing structure [14][15][16][17]. The work of Fazilati [18] presents the effect of delamination in the panel flutter behavior. However, some practical limitations must still be addressed.…”

Section: Introductionmentioning

confidence: 99%

Supersonic Flutter and Buckling Optimization of Tow-Steered Composite Plates

et al. 2019

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The supersonic aeroelastic stability of tow steered carbon reinforced composite panels, in each layer of which the fibers follow curvilinear paths, is assessed. A structural model based on the Rayleigh-Ritz method, combined with the aerodynamic piston theory, is derived to represent the aeroelastic behavior of rectangular plates under different boundary conditions. In this model, the Classical Lamination Theory, considering symmetric stacking sequence and fiber trajectories described by Lagrange polynomials of different orders, is used. In addition, manufacturing constraints, which impose limitations to the feasible fiber trajectories, and the effect of in-plane loads, are also considered in the model. Using a multi-criteria Differential Evolution algorithm, numerical optimization is performed for a variety of scenarios, aiming at increasing the flutter and linear buckling stability margins of tow-steered plates, considering the geometrical parameters defining the fiber trajectories on the layers as design variables. Results obtained for the different optimization scenarios are compared, having a composite plate with unidirectional fibers as the baseline, aiming at evaluating the benefits achieved by the optimum tow-steered plates. Results enable to quantify the stability improvements by exploring fiber steering, which has been shown to be beneficial, even in situations where manufacturing constraints are accounted for.

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Panel flutter of curvilinear composite laminated plates in the presence of delamination

Cited by 17 publications

References 14 publications

Aeroelastic analysis and flutter control of wings and panels: A review

Aeroelastic analysis and flutter control of wings and panels: A review

Numerical modeling of nonlinear vibrations of viscoelastic shallow shells

Supersonic Flutter and Buckling Optimization of Tow-Steered Composite Plates

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