Finite element analysis of large-amplitude panel flutter of thin laminates

Dixon, I.R.; Mei, Chuh

doi:10.2514/3.11606

Cited by 74 publications

(23 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The studies on the supersonic flutter of laminated panels reveal that the flutter oscillation is a coupled mode flutter with high modes coalescence [3,8,19], which is different from the coupled mode flutter of isotropic panels possessing equal amounts of the first and second natural modes [1]. The effects of lay-up schedule, fiber orientation, flow direction, skew angle etc.…”

Section: Introductionmentioning

confidence: 96%

“…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%

See 1 more Smart Citation

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

Xia

2011

Acta Mech Sin

View full text Add to dashboard Cite

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.

show abstract

Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

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

Xia

2011

Acta Mech Sin

View full text Add to dashboard Cite

show abstract

“…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

View full text Add to dashboard Cite

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.

show abstract

“…Applying the finite element method, Mei [4] investigated the supersonic limit-cycle oscillations of two-dimensional panels. Dixon and Mei [5] studied the nonlinear flutter of rectangular composite panels and obtained the limit-cycle response using a 24-dof rectangular plate element and a linearized updated mode with nonlinear time function approximate solution procedure. Carl et al [6] applied the FEM to study the nonlinear flutter characteristics of three-dimensional thin laminated composite panels.…”

mentioning

confidence: 99%

Nonlinear flutter of a two-dimension thin plate subjected to aerodynamic heating by differential quadrature method

2008

View full text Add to dashboard Cite

The problem of nonlinear aerothermoelasticity of a two-dimension thin plate in supersonic airflow is examined. The strain-displacement relation of the von Karman's large deflection theory is employed to describe the geometric non-linearity and the aerodynamic piston theory is employed to account for the effects of the aerodynamic force. A new method, the differential quadrature method (DQM), is used to obtain the discrete form of the motion equations. Then the Runge-Kutta numerical method is applied to solve the nonlinear equations and the nonlinear response of the plate is obtained numerically. The results indicate that due to the aerodynamic heating, the plate stability is degenerated, and in a specific region of system parameters the chaos motion occurs, and the route to chaos motion is via doubling-period bifurcations.

show abstract

Finite element analysis of large-amplitude panel flutter of thin laminates

Cited by 74 publications

References 20 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

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

Nonlinear flutter of a two-dimension thin plate subjected to aerodynamic heating by differential quadrature method

Contact Info

Product

Resources

About