Analytical study of thermal buckling and post-buckling behavior of composite beams reinforced with SMA by Reddy Bickford theory

2021 ◽  
pp. 1045389X2110116
Author(s):  
Mahshad Fani ◽  
Fathollah Taheri-Behrooz
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Composite Structures ◽  
Volume Fraction ◽  
Thermal Buckling ◽  
Constitutive Law ◽  
Beam Deflection ◽  
Buckling Behavior ◽  
Non Linear ◽  
Post Buckling

Shape memory alloys are used in composite structures due to their shape memory effect and phase transformation. The recovery force of the shape memory alloy improves the post-buckling behavior of the structure. In this study, the thermal buckling and post-buckling of Shape Memory Alloy (SMA) hybrid composite laminated beam subjected to uniform temperature distribution is investigated. To this purpose, considering Von-Karman non-linear strain terms for large deformation, the non-linear equations of SMA reinforced beam based on Reddy Bickford theory have been derived. Besides, the recovery stress of the restrained SMA wires during martensitic transformation was calculated based on the one-dimensional constitutive law of the Brinson’s model. A numerical solution using Galerkin’s method has been presented for solving the nonlinear partial differential equations to obtain the critical buckling temperature and transverse deformation of the beam in the post-buckling region in both symmetric and anti-symmetric layups. The effect of SMA volume fraction, pre-strain, the boundary condition of the beam, stacking sequence, and its geometric properties have been studied. The results show that even by adding a small amount of SMA to the composite, the critical buckling temperature increases significantly, and the beam deflection decreases. Besides, using this theory has an evident effect on the anti-symmetric layup, especially for the thick beams.

scholarly journals The Instability Improvement of the Symmetric Angle-Ply and Cross-Ply Composite Plates with Shape Memory Alloy Using Finite Element Method

2014 ◽  
Vol 6 ◽  
pp. 632825 ◽  
Author(s):  
Zainudin A. Rasid ◽  
Rizal Zahari ◽  
Amran Ayob
Keyword(s):  
Finite Element ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Volume Fraction ◽  
Shear Deformation Theory ◽  
Composite Plates ◽  
Element Formulation ◽  
Recovery Stress ◽  
Buckling Behavior ◽  
Post Buckling

Shape memory alloy (SMA) wires were embedded within laminated composite plates to take advantage of the shape memory effect property of the SMA in improving post-buckling behavior of composite plates. A nonlinear finite element formulation was developed for this study. The plate-bending formulation used in this study was developed based on the first order shear deformation theory, where the von Karman's nonlinear moderate strain terms were added to the strain equations. The effect of the SMA was captured by adding recovery stress term in the constitutive equation of the SMA composite plates. Values of the recovery stress of the SMA were determined using Brinson's model. Using the principle of virtual work and the total Lagrangian approach, the final finite element nonlinear governing equation for the post-buckling of SMA composite plates was derived. Buckling and post-buckling analyses were then conducted on the symmetric angle-ply and cross-ply SMA composite plates. The effect of several parameters such as the activation temperature, volume fraction, and the initial strain of the SMA on the post-buckling behavior of the SMA composite plates were studied. It was found that significant improvements in the post-buckling behavior for composite plates can be attained.

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

2010 ◽  
Vol 224 (4) ◽  
pp. 757-769 ◽  
Author(s):  
S K Panda ◽  
B N Singh
Keyword(s):  
Finite Element ◽  
Shape Memory Alloy ◽  
Spherical Shell ◽  
Shape Memory ◽  
Volume Fraction ◽  
Laminated Composite ◽  
Linear Finite Element ◽  
Non Linear ◽  
Post Buckling ◽  
Shell Panel

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.

scholarly journals Thermal Buckling and Post-Buckling Improvements of Laminated Composite Plates Using Finite Element Method

2011 ◽  
Vol 471-472 ◽  
pp. 536-541 ◽  
Author(s):  
Zainudin A. Rasid ◽  
Ayob Amran ◽  
Rizal Zahari ◽  
Faizal Mustapha ◽  
D.L. Majid ◽  
...  
Keyword(s):  
Finite Element ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Element Formulation ◽  
Laminated Composite Plates ◽  
Aerospace Applications ◽  
Post Buckling

Thermal buckling and thermal post-buckling behaviours of laminated composite plates are improved by embedding shape memory alloy wires within laminates of composite plates. The procedure is to use the recovery stress that is induced when the reverse transformation of the shape memory alloy from martensite to austenite phases is constrained. For aerospace applications where the source of the shape memory alloy heating is the high temperature environment itself, a study is conducted to see the effect of shape memory alloy in improving the thermal buckling and post-buckling of composite plates. Due to the temperature dependent nature of the composite matrix and the shape memory alloy, the finite element formulation developed here is in the incremental form. Solving this non-linear model using the developed in-house source code, critical loads are determined and the post-buckling paths of the shape memory alloy composite plates are traced. This study shows that by embedding the shape memory alloy within composite plates, the thermal buckling and post-buckling behaviours of composite plates can be improved substantially.

scholarly journals Flutter and Thermal Buckling Analysis for Composite Laminated Panel Embedded with Shape Memory Alloy Wires in Supersonic Flow

2016 ◽  
Vol 2016 ◽  
pp. 1-12 ◽  
Author(s):  
Chonghui Shao ◽  
Dengqing Cao ◽  
Yuqian Xu ◽  
Hai Zhao
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Volume Fraction ◽  
Plate Theory ◽  
Equations Of Motion ◽  
Thermal Buckling ◽  
Composite Panel ◽  
Limit Cycle Oscillation ◽  
Classical Plate Theory ◽  
Aerodynamic Pressure

The flutter and thermal buckling behavior of laminated composite panels embedded with shape memory alloy (SMA) wires are studied in this research. The classical plate theory and nonlinear von-Karman strain-displacement relation are employed to investigate the aeroelastic behavior of the smart laminated panel. The thermodynamic behaviors of SMA wires are simulated based on one-dimensional Brinson SMA model. The aerodynamic pressure on the panel is described by the nonlinear piston theory. Nonlinear governing partial differential equations of motion are derived for the panel via the Hamilton principle. The effects of ply angle of the composite panel, SMA layer location and orientation, SMA wires temperature, volume fraction and prestrain on the buckling, flutter boundary, and amplitude of limit cycle oscillation of the panel are analyzed in detail.

The Instability Improvement of the Shape Memory Alloy Composite Plates Subjected to In-Plane Parabolic Temperature Distribution

2014 ◽  
Vol 554 ◽  
pp. 32-36 ◽  
Author(s):  
Z.A. Rasid ◽  
R. Zahari ◽  
Amran Bin Ayob
Keyword(s):  
Temperature Field ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Composite Plates ◽  
Thermal Buckling ◽  
Recovery Stress ◽  
Uniform Temperature ◽  
Source Codes ◽  
Temperature Distributions ◽  
Post Buckling

The designs of thin structure components of aerospace vehicles require the consideration of thermal buckling and post-buckling problems. Thermal buckling of the structures in the aerospace environment may occur due to non-uniformly distributed temperature field. A finite element method study on the post-buckling of composite plates with embedded shape memory alloy wires was conducted. The plates were subjected to in-plane and through-thickness non-uniform thermal loadings where the non-uniform temperature distributions considered were parabolic in-plane and linearly varying through-thickness thermal loadings that may act separately or in combination. Recovery stress induced by the shape memory alloy was exploited to improve the thermal buckling behaviours of the composite plates. A non-linear finite element model along with its source codes that considered the recovery stress of the shape memory alloy, the non-uniform temperature field, the temperature dependent properties of the SMA and the composite matrix were developed. The post-buckling paths that showed the effect of the shape memory alloy on the thermal post-buckling behaviour of composite plates were generated using the source codes. It was found that the strain energy tuning method of the shape memory alloy greatly improved the post-buckling behaviour of composite plates subjected to the non-uniform temperature distributions.

Free vibration analysis of hybrid laminated composite cylindrical shells reinforced with shape memory alloy fibers

2019 ◽  
Vol 26 (7-8) ◽  
pp. 610-626
Author(s):  
Morteza Nekouei ◽  
Mehdi Raghebi ◽  
Meisam Mohammadi
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Fundamental Frequency ◽  
Volume Fraction ◽  
Cylindrical Shells ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Free Vibration Analysis ◽  
Constitutive Law ◽  
Composite Cylindrical Shells

In the present paper, vibration behavior of hybrid laminated composite cylindrical shells reinforced with shape memory alloy fibers is investigated. Material properties of shape memory alloy fibers and composites are accurately considered temperature dependent. Thermo-mechanical properties of shape memory alloy fibers with uniform temperature change are calculated using Brinson’s one-dimensional constitutive law. Love’s first approximation and first-order shear deformation theory of shells with the von Kármán type of geometrical non-linearity are used in conjunction with Hamilton’s principle for deriving the equations of motion. The generalized differential quadrature method is employed to solve the coupled partial differential equations. The effects of pre-strain, volume fraction, phase transformation, location of shape memory alloy fibers, boundary conditions and temperature on the fundamental frequency of the hybrid laminated composite cylindrical shells are studied. Results indicate that a small amount of shape memory alloy fibers significantly increases the fundamental frequency and vibration control of the hybrid laminated composite reinforced with shape memory alloy hybrid laminated composite cylindrical shells.

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