Flutter and Thermal Deflection Suppression of Composite Plates Using Shape Memory Alloy

Bin, Duan; Abdel-Motagaly, K.; Guo, Xinyun; Mei, Chuh

doi:10.2514/1.2093

Cited by 8 publications

(6 citation statements)

References 19 publications

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“…Tawfik et al (2000, 2002) used a nonlinear finite element method to investigate the thermal deflection and linear flutter responses of shape memory alloy hybrid laminated composite (SMAHC) plates under aerodynamic and thermal loading, and the results show that the SMA has a great effect on the critical buckling temperature, flutter boundary, and vibration frequencies of SMAHC panel. Guo et al (2004, 2007), Duan et al (2005), Kuo et al (2009, 2012), and Shiau et al (2011) discovered that the critical buckling temperature can be raised greatly, and the post-buckling deflection can be completely suppressed, while the desired flat and stable region in the parameter space composed of the temperature and the dynamic pressure can be greatly enlarged by proper selection of the volume fraction, pre-strain, and alloy composition of SMA in SMAHC plates. Park et al (2004, 2005) and Mirzaeifar et al (2009, 2014) also used a nonlinear finite element method to investigate the vibration behavior of a thermally buckled composite plate embedded with SMA fibers, and similar results were obtained.…”

Section: Introductionmentioning

confidence: 99%

Research on stability and nonlinear vibration of shape memory alloy hybrid laminated composite panel under aerodynamic and thermal loads

Zhang

Sheng

2016

Journal of Intelligent Material Systems and Structures

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The stability and nonlinear vibration of a NiTi shape memory alloy hybrid laminated composite panel under aerodynamic and thermal loads are investigated. The partial differential dynamic equations of the shape memory alloy hybrid laminated composite panel are derived based on the large deformation theory, the first-order piston theory of aerodynamic pressure and a simple constitutive model of shape memory alloy. Then, the general expressions of multimode discrete equations of the shape memory alloy hybrid laminated composite panel are obtained for the first time using Galerkin method. The stability of the shape memory alloy hybrid laminated composite panel is analyzed first based on the Routh–Hurwitz criteria, and the results show that the temperature and aerodynamic pressure parameter plane can be divided into a flat and stable region, a flutter region, and a buckling region, and the flat and stable region can be greatly enlarged as the shape memory alloy volume fraction increases. Meanwhile, numerical results of the dynamic equations show that the shape memory alloy hybrid laminated composite panel can produce various dynamic motions, and the bifurcation characteristics of the responses with temperature obtained by numerical method coincide well with the stability boundaries determined by analytical method.

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Section: Introductionmentioning

confidence: 99%

Research on stability and nonlinear vibration of shape memory alloy hybrid laminated composite panel under aerodynamic and thermal loads

Zhang

Sheng

2016

Journal of Intelligent Material Systems and Structures

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“…Weisshaar et al [1][2] showed that the flutter boundary of the panel with partial SMA layer is significantly increased. Park et al [3] and Duan et al [4] investigated the control of the thermal post-buckling deflection, critical temperature and critical dynamic pressure by using the SMA. Ostachowicz et al [5] studied the effect of SMA fiber on the flutter of the composite plate with delaminations.…”

Section: Introductionmentioning

confidence: 99%

“…However, most of the previous studies were performed based on finite element modeling of structures [3][4][5][6]. It can be seen that few researches presented analytical solutions [1][2] for flutter analysis of the composite panels with SMA.…”

Section: Introductionmentioning

confidence: 99%

“…It can be seen that few researches presented analytical solutions [1][2] for flutter analysis of the composite panels with SMA. Furthermore, it is found that the thermo-mechanical behavior was described by the expression of approximate fitting or use of the approximate data obtained from the curves of SMA [3][4]6]. And some important factors affecting the flutter behaviour of the composite panels with SMA have not studied enough and the time domain response was not provided.…”

Section: Introductionmentioning

confidence: 99%

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An analytical model for flutter behavior of composite panels with shape memory alloy fibers

Ren¹,

Du²,

Ma³

2016

J. vibroeng.

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An analytical model for predicting the effect of shape memory alloys (SMA) on the flutter behavior of composite panels is developed in the frequency and time domains. The laminated plate theory and piston theory are employed to model the aeroelastic response of the composite panels to aerodynamic loads. A thermo-mechanical constitutive equation of SMA proposed by Brinson et al. is used to calculate the recovery stress of the constrained SMA fibers. The approximate solution is obtained for supersonic flutter analysis of the composite panels based on the Galerkin approach. The parametric study is carried out to display the effect of the actuation temperature, volume fraction, the initial strain of SMA fibers and the length to width ratio of the panels on flutter boundaries.

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“…They discretized the model using the FEM and solved it using the Newton-Rapson method. Duan et al [10] investigated aero-thermal post-buckling and flutter for composite panels with and without SMA fibres. Hartl and Lagoudas [11] discussed the SMA and their application in aerospace industries in detail.…”

Section: Introductionmentioning

confidence: 99%

Thermal post-buckling analysis of a laminated composite spherical shell panel embedded with shape memory alloy fibres using non-linear finite element method

Panda

Singh

2010

Proceedings of the Institution of Mechanical Engineers, Part C:

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In this article, the buckling and post-buckling behaviours of a laminated composite spherical shallow shell panel embedded with shape memory alloy (SMA) fibres are studied under a thermal environment. System equations for a laminated composite spherical shell panel embedded with SMA fibres are for the first time derived by modelling the geometric non-linearity in the Green—Lagrange sense and the material non-linearity in SMA fibres in the framework of the higher-order shear deformation theory. The shell panel model is discretized by using a non-linear finite-element approach. The governing algebraic equations are then derived by the variational approach and solved using a direct iterative technique. Influences of the thickness ratio, boundary condition, aspect ratio, curvature ratio, lamination scheme, SMA volume fraction, percentage of prestrain, and amplitude ratio on the buckling and post-buckling temperatures of a laminated composite shell panel with and without SMA have been examined in detail. The results are computed using the present model and compared with those available in the literature.

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Flutter and Thermal Deflection Suppression of Composite Plates Using Shape Memory Alloy

Cited by 8 publications

References 19 publications

Research on stability and nonlinear vibration of shape memory alloy hybrid laminated composite panel under aerodynamic and thermal loads

Research on stability and nonlinear vibration of shape memory alloy hybrid laminated composite panel under aerodynamic and thermal loads

An analytical model for flutter behavior of composite panels with shape memory alloy fibers

Thermal post-buckling analysis of a laminated composite spherical shell panel embedded with shape memory alloy fibres using non-linear finite element method

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