Supersonic flutter characteristics of functionally graded flat panels including thermal effects

Prakash, T.; Ganapathi, M.

doi:10.1016/j.compstruct.2004.10.007

Cited by 138 publications

(62 citation statements)

References 17 publications

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“…Kim [14] developed an analytical technique to investigate the effect of temperature on the vibration characteristics of thick functionally graded rectangular plates, taking into account the temperature-dependence of the material properties. The influence of thermal environment on the critical flutter dynamic pressure of a flat FGM panel was studied by Prakash and Ganapathi [15]. Ibrahim et al [16] developed a frequency-domain solution to predict the flutter limit-cycle oscillation amplitudes of FGM panels under combined aerodynamic and thermal loads.…”

Section: Introductionmentioning

confidence: 99%

Thermo-acoustic random response of temperature-dependent functionally graded material panels

et al. 2010

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A nonlinear finite element model is provided for the nonlinear random response of functionally graded material panels subject to combined thermal and random acoustic loads. Material properties are assumed to be temperaturedependent, and graded in the thickness direction according to a simple power law distribution in terms of the volume fractions of the constituents. The governing equations are derived using the first-order shear-deformable plate theory with von Karman geometric nonlinearity and the principle of virtual work. The thermal load is assumed to be steady state constant temperature distribution, and the acoustic excitation is considered to be a stationary white-Gaussian random pressure with zero mean and uniform magnitude over the plate surface. The governing equations are transformed to modal coordinates to reduce the computational efforts. Newton-Raphson iteration method is employed to obtain the dynamic response at each time step of the Newmark implicit scheme for numerical integration. Finally, numerical results are provided to study the effects of volume fraction exponent, temperature rise, and the sound pressure level on the panel response.

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Section: Introductionmentioning

confidence: 99%

Thermo-acoustic random response of temperature-dependent functionally graded material panels

et al. 2010

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“…The material properties are assumed to be temperature dependent according to the following relation [26]:…”

Section: Numerical Simulation Of Buckling and Post-buckling Of An Fgmmentioning

confidence: 99%

“…The spatial volume fractions of the constituents are optimized so as to maximize either the first or the second natural frequency of the plate. Parkash and Ganapathi [26] adopted the finite element method to investigate the supersonic flutter behavior of flat panels made of functionally graded material under the influence of thermal environment. Temperature dependent material properties were only assumed while calculating material properties through the thickness, but not while increasing the temperature to reach buckling.…”

Section: Introductionmentioning

confidence: 99%

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

Ibrahim¹,

Tawfik

Al-Ajmi

2007

Comput Mech

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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.

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“…It is hypothesized that aerodynamic nonlinearities, not modeled in their work present are the primary cause of these differences. Prakash and Ganapathi [7] investigated the influence of thermal environment on the supersonic flutter behavior of flat panels made of functionally graded materials using the finite element procedure. The structural formulation is based on first-order shear theory and material properties are assumed temperature dependent and graded in the thickness direction according to power law distribution in terms of the volume fractions of the constituents.…”

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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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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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Supersonic flutter characteristics of functionally graded flat panels including thermal effects

Cited by 138 publications

References 17 publications

Thermo-acoustic random response of temperature-dependent functionally graded material panels

Thermo-acoustic random response of temperature-dependent functionally graded material panels

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

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

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