Application of aeroelastic modes on nonlinear supersonic panel flutter at elevated temperatures

Guo, Xinyun; Mei, Chuh

doi:10.1016/j.compstruc.2006.01.041

Cited by 60 publications

(14 citation statements)

References 17 publications

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“…5. By considering eight mode shapes in the chordwise and two mode shapes in spanwise directions, the same solution as presented in [28] can be obtained. Transverse limit cycle oscillation in two different dimensionless aerodynamic pressures are calculated and shown in Fig.…”

Section: -1 Validation Of the Cracked Panel And Aeroelastic Charactementioning

confidence: 77%

“…Now after presenting the validity of linear structural equations of motion by presenting its natural frequencies, the validity of intact aeroelastic panel is investigated. For this purpose, limit cycle oscillation behavior of simply supported isotropic square panel presented by Guo et al [28] is studied. Convergence of the solution in terms of selecting appropriate numbers of modes shapes for square panels with different chord to thickness ratios are shown in Fig.…”

Section: -1 Validation Of the Cracked Panel And Aeroelastic Charactementioning

confidence: 99%

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Effects of all-over part-through cracks on the aeroelastic characteristics of rectangular panels

AsadiGorgi

Dardel

Pashaei

2015

Applied Mathematical Modelling

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In this study, flutter, limit cycle oscillation, and different nonlinear oscillations analyses of rectangular panels with all-over part-through crack are presented. These analyses are carried out for panels in according to first order shear deformation or Mindlin plate theory. The effects of crack's depth and location on various aeroelastic characteristics of moderately thick rectangular panels are accurately studied. These analyses show that for much of crack's depths and locations, the amplitude of nonlinear vibrations are increased. But there are some crack's locations, for them panel has lower amplitude of vibrations with respect to its intact counterpart. With changing the location and depth of crack, the maximum limit cycle oscillation amplitude will be different from intact counterpart. Also cracked panel may exhibit complex oscillations, other than limit cycle oscillation of intact panel. From these analyses, it can be shown that crack has significant influence on flutter boundary, and amplitude of limit cycle oscillation. Nomenclatureܽ Panel chord-wise length ܷ elastic energy ܾ Panel span-wise length ‫,ݔ‬ ‫,ݕ‬ ‫ݖ‬ Coordinates ‫ܦ‬ Plate bending flexible ߫, ߟ, ‫ݓ‬ ഥ non-dimensional coordinates ‫ܧ‬ Panel module of elasticity ߛ Shear strains ‫ܪ‬ Panel thickness ߝ Tensile strain components ℎ Crack thickness ߢ Shear correction factor ݉, ݊ Number of modes shapes for chord-wise and span-wise direction ߣ ி Dimensionless flutter (critical) aerodynamic pressure ‫ܯ‬ Mass matrix ߩ, ߩ Panel and air densities ‫ܭ‬ Stiffness matrix ߥ Poisson's ratio ‫ܮܰ‬ Nonlinear matrix ߱ Dimensionless frequency ‫ܣ‬ cross-sectional area ߱ Dimensionless i'th transverse frequency ‫ܭ‬ Crack stiffness coefficient ߫ Chord wise dimensionless crack location

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Section: -1 Validation Of the Cracked Panel And Aeroelastic Charactementioning

confidence: 77%

Section: -1 Validation Of the Cracked Panel And Aeroelastic Charactementioning

confidence: 99%

Effects of all-over part-through cracks on the aeroelastic characteristics of rectangular panels

AsadiGorgi

Dardel

Pashaei

2015

Applied Mathematical Modelling

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“…It is also noted from Ref. [4] that the flutter bound of the fully simply supported isotropic panel is λ cr = 512. So it can be concluded that for the SSSS panel, AMM is accurate and efficient in the investigation on the flutter characteristics of the supersonic panel.…”

Section: Numerical Simulations and Discussionmentioning

confidence: 99%

“…For complex structures, more modes were needed. Guo and Mei [4] introduced the aeroelastic modes in the analysis of nonlinear panel flutter considering thermal effect. The results showed that the use of aeroelastic modes could reduce the number of coupled nonlinear modal equations significantly.…”

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confidence: 99%

Investigations on the flutter properties of supersonic panels with different boundary conditions

Song

2013

Int. J. Dynam. Control

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Aeroelastic characteristics of supersonic panels with different boundary conditions are analyzed. The classical thin plate theory is used in the structural modeling. The unsteady aerodynamic pressure is evaluated using the supersonic piston theory. To formulate the governing equation of motion for the aeroelastic structural system, Hamilton's principle is carried out. The assumed mode method (AMM) and the finite element method are used to obtain the discrete equation of motion. Frequency-domain method is conducted to analyze the aeroelastic performances of the panel with different boundary conditions. The special flutter properties of panels with elastically restrained boundary condition are also investigated. The accuracy of the AMM in the flutter analysis of panels with different constraints is researched. Aeroelastic characteristics of the panels with different boundary conditions are also investigated.

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“…At supersonic speeds, the skin panel temperatures can reach several hundred degrees due to aerodynamic heating (e.g., 85-108 • C for the Concorde cruising at Mach 2.0, and 141-189 • C for the Quiet Supersonic Platform at Mach 2.4). Due to the combined load of airflow and heating, the flexible skin panels might exhibit large aerothermal deflections [6].…”

Section: Introductionmentioning

confidence: 99%

A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

et al. 2011

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In this paper, the effect of the system parameters on the flutter of a curved skin panel forced by a supersonic/hypersonic unsteady flow is numerically investigated. The aeroelastic model investigated includes the third-order piston theory aerodynamics for modeling the flow-induced forces and the Von Kármán nonlinear strain-displacement relation in conjunction with the Kirchhoff plate hypothesis for the panel structural modeling. Structural non-linearities are considered and are due to the non-linear coupling between out-of-plane bending and in-plane stretching. The effects of thermal degradation and Kelvin's model of structural damping independent on time and temperature are also considered. The aero-thermo-elastic governing equations are developed from the geometrically imperfect non-linear theory of infinitely long two-dimensional curved panels. Computational analysis and discussion of the finding along with pertinent conclusions are presented.

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Application of aeroelastic modes on nonlinear supersonic panel flutter at elevated temperatures

Cited by 60 publications

References 17 publications

Effects of all-over part-through cracks on the aeroelastic characteristics of rectangular panels

Effects of all-over part-through cracks on the aeroelastic characteristics of rectangular panels

Investigations on the flutter properties of supersonic panels with different boundary conditions

A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

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