A higher finite element model in nonlinear panel flutter analysis

Udrescu, Radu

doi:10.2514/6.1998-1843

Cited by 5 publications

(2 citation statements)

References 10 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Liaw [24] used a 48-deg-of-freedom (DOF) rectangular thin-plate finite element to study the nonlinear panel flutter under uniform and sinusoidal temperature distributions. Udrescu [25] developed a 33-DOF triangular finite element to study a simply supported three-dimensional isotropic panel under uniform temperature distribution. The effects of hypersonic aerothermoelastic interactions on panel behavior have been investigated thoroughly by Culler and McNamara [26,27], Miller et al [28], and Crowell et al [29].…”

Section: B Temperature Effectsmentioning

confidence: 99%

Supersonic Aerothermoelastic Nonlinear Flutter Study of Curved Panels: Frequency Domain

Ghoman

Azzouz

2012

Journal of Aircraft

View full text Add to dashboard Cite

This paper describes the development of a consistent finite element formulation and an efficient solution procedure to investigate the nonlinear flutter of curved panels at yawed supersonic flow and at elevated temperatures. A finite element frequency domain method is developed to predict the preflutter behavior and the flutter onset of curved panels subjected simultaneously to aerodynamic and thermal loading. The Marguerre plate theory, the von Kármán large deflection theory, quasi-steady first-order piston theory, and quasi-static thermoelasticity are used in the formulation. The principle of virtual work is applied to develop the equations of motion of the fluttering system in structural degrees of freedom. The Newton-Raphson method is used to determine the panel deflection under the static thermoaerodynamic loading, and an eigenvalue solution is employed for predicting the flutter critical dynamic pressure for curved panels of different height-rises. Flutter coalescence frequencies and damping rates of the fluttering curved system are investigated for three-dimensional curved panels under increasing dynamic pressure and uniform or linearly varying temperature gradient loading. The results showed that the preflutter panel behavior and the flutter onset are significantly altered when temperature effects are included in the formulation.

show abstract

Section: B Temperature Effectsmentioning

confidence: 99%

Supersonic Aerothermoelastic Nonlinear Flutter Study of Curved Panels: Frequency Domain

Ghoman

Azzouz

2012

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…With the use of von Kármán plate theory, the maximum deflection is of order of plate thickness. The finite element system equations of motion for nonlinear flutter of a laminated composite panel at an arbitrary yawed supersonic flow angle K and temperature distribution DT can be expressed in the matrix form [2,[4][5][6][8][9][10][11][12][13] as The parameters k, C a and K are the non-dimensional dynamic pressure, non-dimensional aerodynamic damping, and flow yaw angle, respectively, with k and C a defined as [4,10] k ¼ 2q a a 3 bD 110…”

Section: System Equations In Structural Node Dofmentioning

confidence: 99%

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

Guo

Mei

2006

Computers & Structures

View full text Add to dashboard Cite

Enhanced Aeroelastic Analysis of Panels Under Transitory Hypersonic Flow Conditions

Udrescu

Surace

2000

AIAA Journal

View full text Add to dashboard Cite

A higher finite element model in nonlinear panel flutter analysis

Cited by 5 publications

References 10 publications

Supersonic Aerothermoelastic Nonlinear Flutter Study of Curved Panels: Frequency Domain

Supersonic Aerothermoelastic Nonlinear Flutter Study of Curved Panels: Frequency Domain

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

Enhanced Aeroelastic Analysis of Panels Under Transitory Hypersonic Flow Conditions

Contact Info

Product

Resources

About