This paper develops a novel and simple analytical model to investigate the bending response of superelastic shape memory alloy (SMA) laminated composite cantilever beam during a complete loading/unloading cycle based on ZM's three-dimensional (3D) thermomechanical model for SMAs and Timoshenko beam theory. The laminated composite beam configuration is formed by two SMA layers bonded to one elastic core layer. The results show a superelastic behavior of the composite. The moment-curvature response, martensite distribution along vertical direction, stress distribution along vertical and axial direction, tip deflection of the composite are revealed. The effects of temperature, thickness ratio and stiffness ratio on the moment-curvature response are also investigated. 3D finite element analysis (FEA) is carried out in parallel to validate against results obtained from analytical and exact numerical models. A good agreement is obtained. Whereby the maximum observed difference in terms of curvature is 7% between analytical and 3D FEA data, and 0.5% between analytical and accurate numerical solutions at moment M e = 0.181 N . m during the loading cases. This novel work sheds light on the fundamental and deep knowledge of SMA composite's static bending behavior. That will be very helpful and significant for other researchers to furtherly investigate on dynamical behavior of this and other SMA laminated composite configurations.

Bending models for superelastic shape memory alloy laminated composite cantilever beams with elastic core layer

Nonlinear modeling of electro-aeroelastic dynamics of composite beams with piezoelectric coupling

Aeroelastic assessment of cracked composite plate by means of fully coupled finite element and Doublet Lattice Method

In the present work, an analytical investigation is introduced to determine the aeroelastic behavior of unswept, rectangular wings simulated by cantilevered composite plates using energy formulation and incompressible aerodynamic theory. Modified higher order shear deformation theory is used in the structural formulation. Doublet point method is used to solve the subsonic unsteady flow over the proposed rectangular wing. The flutter and divergence velocities are obtained using U-g method, which are validated by the analytical, finite element, wind tunnel test results available in the literature. The effect of composite fiber orientation on natural frequency, flutter and divergence speeds is discussed.

https://asat.journals.ekb.eg/article_22181_dc7c6bc9edf20cd1d8f304f016db986c.pdf

Flutter and Divergence Characteristics of Composite Plate Wing

https://research-information.bris.ac.uk/files/172921569/1_s2.0_S0263822318314387_main.pdf

A robust and reliability-based aeroelastic tailoring framework for composite aircraft wings

In the present work, static deformation, dynamic characteristic, and time response of laminated composite plates with surface-bonded shape-memory alloy (SMA) sheets are modeled. A modified higher order shear deformation theory with Ritz method is utilized. The energy balance equations are used to formulate the nonlinear heat transfer governing equations. The time response of the SMA/elastomer plate and the deflection as well as dynamic characteristics before and after activation of the SMA is computed. A Mathematica code is developed to analyze different plate problems. Parametric studies are performed for proposed structure system to demonstrate the effect of thickness ratio, aspect ratio, material properties, thermal expansion coefficient, electric input power, and thickness of SMA sheet on the transverse deflections, natural frequencies, and response time of the SMA layer. The obtained results are compared to the available studies solved by different theories.

Modeling and analysis of laminated shape memory alloy composite plates

In the present work, a modified higher-order shear deformation theory is developed to analyze isotropic and composite plates to obtain the static response as well as dynamic characteristics using Ritz solution technique. The displacement-field equations of Lo’s higher order shear deformation theory are modified by representing the total rotation of the normal to the mid-plane by two components, bending and shear rotations. The model is valid for thin and thick plates. The plates are subjected to mechanical loads with different types of boundary conditions. A Mathematica code is developed to analyze different plate problems. The obtained results are compared to the available studies solved by different theories and finite element methods. It is shown that the obtained results are accurate using less number of degrees of freedom.

https://asat.journals.ekb.eg/article_22182_f011491e888dc20288213c3496e04eeb.pdf

Modeling and Analysis of Laminated Composite Plate Using Modified Higher Order Shear Deformation Theory

A Laminated composite plate with embedded shape memory alloy wires are modeled and analyzed based on the modified higher-order shear deformation theory. The Hamilton’s principle in conjunction with Brinson’s constitutive model is used to obtain the three-dimensional governing equations. The Ritz solution technique is used to get the static response as well as the dynamic characteristics of the proposed plates. A simply-supported and cantilevered plates subjected to mechanical loads are used in the analysis with a prepared program using Mathematica langue. Parametric studies are conducted to demonstrate the effect of plate dimensions, fiber orientation angle and volume fraction of composite fibers and shape memory alloy wires, on the activated plate natural frequencies. The obtained results are compared to the available studies solved by different theories and found convenient.

https://asat.journals.ekb.eg/article_22951_ffee3007ce87acc2126214f678cc08f2.pdf

Hany M. Negm

Papers

Flutter and Divergence Characteristics of Composite Plate Wing

Modeling and analysis of laminated shape memory alloy composite plates

Modeling and Analysis of Laminated Composite Plate Using Modified Higher Order Shear Deformation Theory

Modeling and Analysis of Laminated Composite Plates Embedded with Shape Memory Alloy Wires