Flow Angle, Temperature, and Aerodynamic Damping on Supersonic Panel Flutter Stability Boundary

Cheng, Guangfeng; Lee, Y. Y.; Mei, Chuh

doi:10.2514/2.3116

Cited by 18 publications

(3 citation statements)

References 22 publications

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“…ϕ i (x) = sin iπx is set as the trial function that satisfies boundary condition (6), and q i (τ) is the generalized coordinates. Then the displacement variable of the two dimensional panel is expressed as follows:…”

Section: Differential Equation Of Heated Panel Flutter In Supersonic mentioning

confidence: 99%

“…Cheng and Mei et al studied all of the possible types of panel behavior by means of finite time-domain model formulation. In addition, they investigated the effects of airflow declination, temperature change and aerodynamic damping on the stable boundary of panel flutter [5,6]. Azzouz and Mei provided new insights of curved panels flutter, and Newton-Raphson iteration and eigenvalue solutions were used to determine the panel deflection and flutter critical dynamic pressure, respectively [7].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Hopf Bifurcation of Heated Panels Flutter in Supersonic Flow

Cao

Yao

2019

Mathematics

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A differential equation of panel vibration in supersonic flow is established on the basis of the thin-plate large deflection theory under the assumption of a quasi-steady temperature field. The equation is dimensionless, and the derivation of its second-order Galerkin discretization yields a four-dimensional system. The algebraic criterion of the Hopf bifurcation is applied to study the motion stability of heated panels in supersonic flow. We provide a supplementary explanation for the proof process of a theorem, and analytical expressions of flutter dynamic pressure and panel vibration frequencies are derived. The conclusion is that the algebraic criterion of Hopf bifurcation can be applied in high-dimensional problems with many parameters. Moreover, the computational intensity of the method established in this work is less than that of conventional eigenvalue computation methods using parameter variation.

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Section: Differential Equation Of Heated Panel Flutter In Supersonic mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Hopf Bifurcation of Heated Panels Flutter in Supersonic Flow

Cao

Yao

2019

Mathematics

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“…Thus, it is important to study this type of instability characteristics in the analysis of structural components. In this regard, Cheng et al 1 investigated the supersonic flutter of composite plates under aerodynamic load, using the finite element method (FEM). Navazi and Haddadpour 2 performed the aerothermoelastic analysis of functionally graded material (FGM) panels based on classical plate theory (CPT) by using Galerkin’s approach.…”

Section: Introductionmentioning

confidence: 99%

Effects of porosity distribution and piezoelectric layers on natural frequencies and unsteady aerodynamic pressure of smart thick porous plates

Bahaadini,

Javaheri,

Majidi-Mozafari

et al. 2023

Journal of Low Frequency Noise, Vibration and Active Control

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In this paper, the effects of porosity distribution and piezoelectric layers on the natural frequencies and flutter aerodynamic pressure of smart thick porous plates in supersonic airflow are studied. Based on the third-order shear deformation plate theory and first-order piston theory, thick functionally graded porous plates embedded by piezoelectric layers are investigated. The effective porous material properties, such as Young’s modulus and mass density are considered to vary along the thickness direction. The aeroelastic governing equations of motion are obtained using Hamilton’s principle and Maxwell’s equation. By applying Galerkin’s approach, the partial differential governing equations are transformed into a set of ordinary differential equations. The results indicate that the unsteady aerodynamic pressure and natural frequencies decrease as the porosity coefficient increases. Furthermore, the symmetric porosity distribution predicts the highest unsteady aerodynamic pressure and natural frequencies for porous plates. Besides, the results show that the porous plate enclosed by piezoelectric layers in open circuit condition has higher flutter aerodynamic pressure and natural frequencies than the similar plate in closed circuit condition.

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