Improving the Aeroelastic Flutter Characteristics of Supersonic Beams Using Piezoelectric Material

Li, Fengming; Chen, Zhaobo; Cao, Dengqing

doi:10.1177/1045389x11403820

Cited by 15 publications

(7 citation statements)

References 52 publications

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“…where ρ ∞ , U ∞ , and M ∞ are the air density, free stream velocity, and Mach number, respectively. The non-dimensional aerodynamic pressure ( λ ) is usually used to obtain the flutter boundary (Li et al, 2011; Seyyed et al, 2012). Thus, equations (25) and (26) can be redefined as…”

Section: Mathematical Modelingmentioning

confidence: 99%

Aeroelastic analysis of a sandwich panel with partially treated magneto-rheological fluid core

Asgari

Rokn-Abadi

Yousefi

et al. 2018

Journal of Intelligent Material Systems and Structures

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This study considers the aeroelastic instability of a partially treated magneto-rheological fluid sandwich panel in supersonic airflow. The linear first-order piston theory is used for modeling the aerodynamic pressure. Using classical Hamilton’s principle along with the finite element method, the equations of motion are derived. The critical value of the non-dimensional aerodynamic pressure is obtained by traditional p-method scheme. The validity of the finite element formulation is examined through comparison with those obtained from the assumed mode formulation and the available results in the literature. Various parametric studies including the effects of applied magnetic field, core and constraining layer thicknesses are examined for several configurations of the core at simply-supported and clamped–clamped boundary conditions. The results show that the critical non-dimensional aerodynamic pressure of the sandwich panel is influenced not only by the magnetic field strength, core and constraining layer thicknesses but also strongly by the configuration of the core.

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Section: Mathematical Modelingmentioning

confidence: 99%

Aeroelastic analysis of a sandwich panel with partially treated magneto-rheological fluid core

Asgari

Rokn-Abadi

Yousefi

et al. 2018

Journal of Intelligent Material Systems and Structures

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“…In aerospace engineering, it is a necessity to have a fair prediction for the critical velocity for each part of high-speed aircrafts and missiles. Thus, there is a considerable number of papers about aeroelastic stability characteristics of the structures with different shapes such as beam, [24][25][26] rectangular plate, 27,28 skew plate [29][30][31] and trapezoidal plate. [32][33][34] In comparison with these types of structures, there are less number of works regarding aeroelastic stability analysis of cylindrical and conical shells and panels.…”

Section: Introductionmentioning

confidence: 99%

Flutter prediction of cylindrical sandwich panels with saturated porous core under supersonic yawed flow

Akbari

Azadi

Fahham

2020

Proceedings of the Institution of Mechanical Engineers, Part C:

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Supersonic flutter characteristics of cylindrical sandwich panels made of a saturated functionally graded porous (FGP) core and two homogeneous face sheets are studied in this paper based on the Biot’s poroelasticity theory. The third-order shear deformation theory (TSDT) is used to model the panel and the piston theory is hired to estimate the aerodynamic pressure create by the supersonic fluid flow. First, the set of the governing equations are solved numerically via generalized differential quadrature method (GDQM) and natural frequencies are calculated for various boundary conditions. Then, convergence of the solution is confirmed and its accuracy is demonstrated by comparing the results with those reported by other authors. Finally, the effects of geometrical parameters of the panel, thickness of the porous core, porosity distribution pattern, porosity parameter (size of pores), compressibility of pore fluid and yaw angle (fluid flow direction) on the flutter boundaries of FGP sandwich panels are investigated.

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“…Kouchakzadeh et al [30] analyzed the aerodynamic modeling of structures by applying the classical plate theory along with the von Karman nonlinear strains and linear piston theory. Li et al [31] used the piezoelectric material to increase the flutter velocities of the supersonic beams and adopted the supersonic piston theory to evaluate the aerodynamic pressure. Kuo [32] investigated the influence of variable fiber spacing on the supersonic flutter of rectangular composite plates and later also [33] discussed the effects of hybrid fiber distribution on the critical buckling temperature, natural frequencies, and flutter boundary of composite laminates by using the finite element method.…”

Section: Introductionmentioning

confidence: 99%

Influence of Piezoelectric Performance on Nonlinear Dynamic Characteristics of MFC Shells

2019

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Based on the structures of unmanned aerial vehicle (UAV) wings, nonlinear dynamic analysis of macrofiber composite (MFC) laminated shells is presented in this paper. The effects of piezoelectric properties and aerodynamic forces on the dynamic stability of the MFC laminated shell are studied. Firstly, under the flow condition of ideal incompressible fluid, the thin airfoil theory is employed to calculate the effects of the mean camber line to obtain the circulation distribution of the wings in subsonic air flow. The steady aerodynamic lift on UAV wings is derived by using the Kutta–Joukowski lift theory. Then, considering the geometric nonlinearity and piezoelectric properties of the MFC material, the nonlinear dynamic model of the MFC laminated shell is established with Hamilton’s principles and the Galerkin method. Next, the effects of electric field, external excitation force, and nonlinear parameters on the stability of the system are studied under 1 : 1 internal resonance and the effects of material parameters on the natural frequency of the structure are also analyzed. Furthermore, the influence of the aerodynamic forces and electric field on the nonlinear dynamic responses of MFC laminated shells is discussed by numerical simulation. The results indicate that the electric field and external excitation have great influence on the structural dynamic responses.

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Improving the Aeroelastic Flutter Characteristics of Supersonic Beams Using Piezoelectric Material

Cited by 15 publications

References 52 publications

Aeroelastic analysis of a sandwich panel with partially treated magneto-rheological fluid core

Aeroelastic analysis of a sandwich panel with partially treated magneto-rheological fluid core

Flutter prediction of cylindrical sandwich panels with saturated porous core under supersonic yawed flow

Influence of Piezoelectric Performance on Nonlinear Dynamic Characteristics of MFC Shells

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