Effects of flow angularity on nonlinear supersonic flutter of composite panels

Abdel-Motagaly, K.; Chen, R.; Mei, Chuh

doi:10.2514/6.1999-1433

Cited by 2 publications

(3 citation statements)

References 10 publications

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“…(2), (4), (8) and (9) into Eq. (11), the governing equation of thermal post-buckling deflection can be obtained in terms of transverse deflection, {W b }, and the inplane deflection, {W m }.…”

Section: Governing Equation Of the Thermal Post-buckling Deflectionmentioning

confidence: 99%

“…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%

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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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Section: Governing Equation Of the Thermal Post-buckling Deflectionmentioning

confidence: 99%

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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“…Liaw (1997) studied the geometrically nonlinear supersonic flutter of thin laminated composite plate structures subjected to thermal loads. Abdel-Motagaly et al (1999) investigated the effect of arbitrary flow direction on the large amplitude supersonic flutter of moderately thick composite panels, using the von Karman strain-displacement relation to account for large amplitude limit-cycle oscillations. The nonlinear finite element formulation introduced by Mei (1977) was the basis on which Dixon and Mei (1993), and Xue and Mei (1993) built their finite element models to analyze the flutter boundaries, the limit-cycle oscillations, and the thermal problems.…”

Section: Panel Fluttermentioning

confidence: 99%

Thermal buckling and nonlinear flutter behavior of shape memory alloy hybrid composite plates

Ibrahim

Tawfik

Negm

2010

Journal of Vibration and Control

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A new nonlinear finite element model is provided for the nonlinear flutter response of shape memory alloy (SMA) hybrid composite plates under the combined effect of thermal and aerodynamic loads. The nonlinear governing equations for moderately thick rectangular plates are obtained using first-order shear-deformable plate theory, von Karman strain-displacement relations and the principle of virtual work. To account for the temperature dependence of material properties, the thermal strain is stated as an integral quantity of thermal expansion coefficient with respect to temperature. The aerodynamic pressure is modeled using the quasi-steady first-order piston theory. Newton-Raphson iteration method is employed to obtain the thermal post-buckling deflection, while the linearized updated mode method is implemented in predicting the limit-cycle oscillation at elevated temperatures. Numerical results are presented to show the thermal buckling and flutter characteristics of SMA hybrid composite plates, illustrating the effect of the SMA volume fraction and pre-strain value on the aero-thermo-mechanical response of such plates.

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Effects of flow angularity on nonlinear supersonic flutter of composite panels

Cited by 2 publications

References 10 publications

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

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

Thermal buckling and nonlinear flutter behavior of shape memory alloy hybrid composite plates

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