Laminated Hybrid Composite Plates Research Articles

Nanoparticle effects on post-buckling behaviour of patched hybrid composites

Abstract In this study, the effect of particle additive on buckling behaviour in laminated hybrid composite plates was investigated numerically and experimentally for patched samples. In the experimental study, carbon-aramid woven fabric was chosen as the hybrid material and composite plate production was carried out in a temperature-controlled vacuum infusion production unit. The circular holed specimens were patched on one face with the wet patch and the adhesion performance under buckling load was investigated. The buckling test results for composite plates with and without nanoparticle added to patch matrix material were compared. In numerical study, the buckling analysis of composite plates patched with nano-additive and without nano-additive wet patch method was performed with the finite element method. The numerical results obtained in the nonlinear buckling analysis for plates and the experimental results were compatible with each other. Addition of 1 wt% carbon nano tube (CNT) and graphene to the patch material with fiber angle parallel to the loading direction increased the damage loads by 22.5 and 12.6 wt%, respectively, compared to the non-additive patch. Adding 2 wt% CNT increased damage loads by 50%, while adding 2 wt% graphene reduced damage loads only 1%.

Effect of Carbon Nanotubes Volume Fraction on the Deflections and Stresses of Laminated Hybrid Composite Plates using First-Order Shear Deformation Theory

Carbon Nanotubes reinforced composite materials are widely used in aerospace engineering due to high strength-to-weight ratios, which can be tailored per requirements. The behaviour of the composite structures depends on various factors like, Lamination scheme, Ply orientation and loading conditions. In the present work, Static deflection and stresses analysis of a Carbon Nano Tube reinforced laminated hybrid composite plate extends the First Order Shear Deformation Theory with variable ply angles and volume fractions of CNT. A micromechanics model based on the Mori-Tanaka method is used to calculate the properties of CNT reinforced laminate. In this analysis, hybrid composite plates mainly consist of Graphite/epoxy, Kevlar/epoxy and CNT/ polystyrene sub-laminates. The lamination scheme and CNT volume fraction play a vital role in the non-dimensional deflections and stresses. The main intention of this work is to enhance the suitability of CNT reinforced Hybrid composite plates under static loading for structural applications.

Deformation of Carbon Nano Tubes Reinforced Hybrid Laminated Composite Plates induced by Piezoelectric Actuators

Piezoelectric materials, typically used as intelligent materials, can respond according to the design demands of the composite structures autonomously. The excitation of piezoelectric actuators generates the bending effect on the hybrid composite plates. An analytical methodology is developed to calculate the displacements of simply supported laminated composite plates induced by piezoelectric actuators and validate the results by generating MATLAB code. Further, the laminated hybrid composite plates reinforced with carbon nanotubes(CNT) are excited by piezoelectric actuators bonded to the surface on both sides with a variable electrical voltage across the thickness. The effects of location, size and thickness ratio of piezoelectric actuators on the deflection of hybrid composite plates are carried out by extending the code. The transverse displacements vary linearly with the applied voltage and size of the piezoelectric actuators. The effect of CNT volume fraction and the position of CNT lamina plays a vital role in deflections, and also it is observed that maximum displacements decrease rapidly as thickness ratio increases from 0.5 to 5 and from 10 to 50, the maximum displacements gradually decrease. Hence, it illustrated that the present technique provides a simple solution for predicting and controlling the deformed shape of reinforced hybrid composite plates induced by distributed piezoelectric actuators.

Sonlu Elemanlar ve İstatistiksel Yöntemler Kullanılarak Ankastre Tabakalı Hibrit Kompozit Plakaların Burkulma Analizi

In this study, the critical buckling load of hybrid composite plates with three layers was analyzed using numerical and statistical methods. Laminated hybrid composite plates were designed using glass-epoxy, boron-epoxy, carbon-epoxy, and metal. The outermost layers of the plates were modelled using fiber reinforced composite materials whereas the innermost layer of plates was created using Aluminum material (Al2024-T3). Numerical buckling behavior was calculated using finite element software ANSYS. Analysis of signal-to-noise ratio was utilized to decide the effects and optimal levels of the plates and their fiber orientation angles on buckling load. Analysis of variance at the 95 % confidence level was employed to indicate the control factors which have significant effect on the buckling responses.

The investigation of quasi-static indentation effect on laminated hybrid composite plates

Present study aims to investigate quasi-static indentation (QSI) behavior of fiber reinforced hybrid composites in order to develop basic understanding of low velocity impact events. The goal of QSI tests from this study is to explore energy absorption, and load carrying capacity incorporating two and three different combinations of fibers. Major reinforcing fibers were selected as Kevlar with twill weave, carbon and S-glass fibers with plain weave for designing of hybrid composites. Failure modes and extension of damage mechanisms were characterized by observing the surfaces of the indented samples, and damage assessment was identified through the thickness by the cutting of test samples. The results from this study showed that failure mechanisms in hybrid samples were significantly affected by stacking sequence of the fibers as well as fiber types.

Analysis of Shape Memory Alloy Hybrid Composite Plates under Low Velocity Impact

This paper presents the analysis of smart hybrid composite plate with embedded shape memory alloy (SMA) wires subjected to low-velocity impact. The SMA wires were embedded within the layers of the composite laminates and the numerical calculation was used in the impact analyses of the laminated hybrid composite plate. The laminated plate theory, first-order shear deformation theory and minimal potential energy principle was utilized to solve the governing equations of the hybrid composite plate analytically. Energy absorption of hybrid composites can be successfully analyzed using analysis of variance (ANOVA). The results indicated that temperature effect is significant during the transition phase and SMA can effectively improve impact-resistance of the hybrid composite laminated plate. In addition, this hybrid structure is an advanced design concepts that can strengthen the impact resistance capability and enhance the carrying loading efficiency of the structure.

On the Thermal Buckling Behavior of Laminated Hybrid Composite Plates Due to Square/Circular Cut-Outs

Cut-outs like circular, rectangular, elliptical, triangular are generally used in composite structures due to access ports for mechanical and electrical systems, damage inspection, to serve as doors and windows, and sometimes to reduce the overall weight of the structure. In this paper the effects of cut-outs on the thermal buckling behavior of hybrid composite plates in cross-ply and angle-ply laminate are presented. The effects of eccentric cut-out size in different plate aspect ratios and boundary conditions on the thermal buckling behavior of the cross-ply and angle-ply laminated hybrid composite plates are also investigated. Finite element analysis is also performed to calculate thermal buckling temperatures for Kevlar/Epoxy, Boron/Epoxy and E-glass/Epoxy. Several outcomes and behavioral characteristics are discussed. These outcomes include the effects of cut-out size, shape, plate aspect ratio and boundary conditions.

Nonlinear dynamic analysis of a laminated hybrid composite plate subjected to time-dependent external pulses

Nonlinear dynamic responses of a laminated hybrid composite plate subjected to time-dependent pulses are investigated. Dynamic equations of the plate are derived by the use of the virtual work principle. The geometric nonlinearity effects are taken into account with the von Kármán large deflection theory of thin plates. Approximate solutions for a clamped plate are assumed for the space domain. The single term approximation functions are selected by considering the nonlinear static deformation of plate obtained using the finite element method. The Galerkin Method is used to obtain the nonlinear differential equations in the time domain and a MATLAB software code is written to solve nonlinear coupled equations by using the Newmark Method. The results of approximate-numerical analysis are obtained and compared with the finite element results. Transient loading conditions considered include blast, sine, rectangular, and triangular pulses. A parametric study is conducted considering the effects of peak pressure, aspect ratio, fiber orientation and thicknesses.

Natural frequency and buckling optimization of laminated hybrid composite plates using genetic algorithm and simulated annealing

In this study, genetic algorithm and simulated annealing are used to maximize natural frequency and buckling loads of simply supported hybrid composite plates. The aim of the study is to use two di...

BEHAVIOUR OF CROSS - PLY LAMINATED HYBRID COMPOSITE PLATES WITH AN INCLINED CRACK SUBJECTED TO A UNIFORM TEMPERATURE RISE

Thermal buckling analysis of symmetric and antisymmetric cross-ply laminated hybrid composite plates with an inclined crack subjected to a uniform temperature rise are presented in this paper. The first-order shear deformation theory in conjunction with variational energy method is employed in the mathematical formulation. The eight-node Lagrangian finite element technique is used for obtaining the thermal buckling temperatures of hybrid composite laminates. The effects of crack size and lay-up sequences on the thermal buckling temperatures for symmetric and a antisymmetric plates are investigated. The results are shown in graphical form for various boundary conditions. Finally , from this paper, the following main results have been found from which the buckling temperature is affected the larger crack length more than the small crack length, together with other result that the buckling temperature of the plate for every perforation angle is to increase while crack length is increasing

Stability of parametric vibrations of hybrid composite plates

In this paper, the dynamic stability of laminated hybrid composite plates subjected to periodic uniaxial stress and bending stress is studied. The governing equations of motion of Mathieu-type are established by using the Galerkin method with reduced eigenfunctions transforms. Based on Bolotin's method the regions of dynamic instability of laminated hybrid composite plates are determined by solving the eigenvalue problems. The effects of layer thickness ratio, layer number, core material and load parameter on the dynamic instability of laminated hybrid composite plates are investigated and discussed.

Dynamic Response of Smart Hybrid Composite Plate Subjected to Low-Velocity Impact

In this article, the response of rectangular smart hybrid composite plate subjected to low velocity impact is studied and the effect of some geometrical and material parameters on the response of the composite plate embedded with shape memory alloy (SMA) wires is investigated. The interaction between the impactor and the composite plate is considered in the impact analysis. The SMA wires are embedded within the layers of the composite laminate. The effect of the SMA wires on contact force history, deflection, in-plane strains and stresses of the structure was studied. The classical first-order shear deformation theory (FSDT) as well as the Fourier series method is utilized to solve the governing equations of the composite plate analytically. The interaction between the impactor and the plate is modeled with the help of two degrees-of-freedom system, consisting of springs-masses. The Choi's linearized Hertzian contact model is used in the impact analysis of the laminated hybrid composite plate. The simultaneous application of the FSDT, Fourier series method, springs-masses and Choi's linearized contact model helps to get a complete model and more accurate result and save computational time and effort for the analysis of the composite structures subjected to the transverse impact. The results indicated that some of the geometrical and material parameters like the volume fraction, the orientation and the through thickness location of the SMA wires, the longitudinal to transverse elastic modulus ratio of the plate and the material type of composite medium are some of the important factors affecting the impact process and the design of the structures.

Low-velocity impact response of active thin-walled hybrid composite structures embedded with SMA wires

Effect of some important parameters on low-velocity impact response of the active thin-walled hybrid composite plates embedded with the shape memory alloy (SMA) wires is investigated in this paper. The interaction between the impactor and the composite plate is considered in the impact analysis. The SMA wires are embedded within the layers of the composite laminate. The effect of the SMA wires on contact force history, deflection, in-plane strains and stresses of the structure was studied. The first-order shear deformation theory as well as the Fourier series method is utilized to solve the governing equations of the composite plate analytically. The interaction between the impactor and the plate is modeled with the help of two degrees-of-freedom system, consisting of springs-masses. The Choi's linearized Hertzian contact model is used in the impact analysis of the laminated hybrid composite plate. The results indicate that some of the important geometrical and physical parameters like the SMA volume fraction, orientation of composite medium fibers, impactor mass, impactor velocity, and length-to-thickness ratio of the plate ( a/h ratio) are important factors affecting the impact process and the design of structures.

Effect of smart stiffening procedure on low-velocity impact response of smart structures

Abstract The paper presents the response of smart hybrid composite plate subjected to low-velocity impact. The low-velocity impact response of the composite plate embedded with shape memory alloy (SMA) wires is investigated. The SMA wires are embedded within the layers of the composite laminate. The first-order shear deformation theory as well as the Fourier series method is utilized to solve the dynamic governing equations of the hybrid composite plate analytically. The interaction between the impactor and the plate is modeled with the help of two degrees-of-freedom system, consisting of springs-masses. The Choi's linearized Hertzian contact model is used in the impact analysis of the laminated hybrid composite plate. The stiffness of the composite structures classified into two new groups. Interactive and non-interactive effects of these stiffnesses are studied too. In addition, a procedure named smart stiffening procedure (SSP) was used to improve the impact resistance of the composite structures. It was seen that by using of the SSP, the mechanical characteristics of the structure could be improved the most.

Mechanical Buckling Behavior of Hybrid Laminated Composite Plates with Inclined Crack

Buckling analysis of symmetric and antisymmetric cross-ply laminated hybrid composite plates with an inclined crack subjected to a uniform compression is investigated in this article. The first-order shear deformation theory in conjunction with the variational energy method is employed in the mathematical formulation. The effects of crack size, crack inclination angle, and lay-up sequences on the buckling loads are investigated. The results are shown in graphical form for various conditions.

Thermal buckling behavior of cross-ply hybrid composite laminates with inclined crack

Thermal buckling analysis of symmetric and antisymmetric cross-ply laminated hybrid composite plates with an inclined crack subjected to a uniform temperature rise are presented in this paper. The first-order shear deformation theory in conjunction with variational energy method is employed in the mathematical formulation. The eight-node Lagrangian finite element technique is used for obtaining the thermal buckling temperatures of hybrid composite laminates. The effects of crack size and lay-up sequences on the thermal buckling temperatures for symmetric and antisymmetric plates are investigated. The results are shown in graphical form for various boundary conditions.

Thermal buckling of hybrid angle-ply laminated composite plates with a hole

In this paper, thermal buckling analysis of symmetric and antisymmetric laminated hybrid composite plates with a hole subjected to a uniform temperature rise for different boundary conditions is presented. The first-order shear deformation theory in conjunction with variational energy method is employed in mathematical formulation. The eight-node Lagrangian finite element technique is used for obtaining the thermal buckling temperatures of glass–epoxy/boron–epoxy hybrid laminates. The effects of hole size, lay-up sequences and boundary conditions on thermal buckling temperatures are investigated. The results are shown in graphical form for various boundary conditions.

Thermal Buckling Behavior of Hybrid-Composite Angle-Ply Laminated Plates with an Inclined Crack

A thermal buckling analysis of symmetric and antisymmetric angle-ply laminated hybrid composite plates with an inclined crack subjected to a uniform temperature rise is presented in this paper. The first-order shear deformation theory in conjunction with the variational energy method is employed in mathematical formulations. The eight-node Lagrange finite-element technique is used for determining the thermal buckling temperatures of hybrid laminates. The effect of crack size and stacking sequences on the temperatures is investigated.

Thermal buckling of hybrid laminated composite plates with a hole

Thermal buckling analysis of symmetric and antisymmetric cross-ply laminated hybrid composite plates with a hole subjected to a uniform temperature rise for different boundary conditions are presented in this paper. The first-order shear deformation theory in conjunction with variational energy method is employed in the mathematical formulation. The eight-node Lagrangian finite element technique is used for finding the thermal buckling temperatures of hybrid laminates. The effects of hole size, lay-up sequences and boundary conditions on the thermal buckling temperatures are investigated. The results are shown in graphical form for various conditions.

Analysis of nonlinear vibration of hybrid composite plates

Using the Lagrangian equation, the nonlinear vibration analysis of laminated hybrid composite plates is carried out. The effects of stacking sequences, aspect ratios, number of modes, number of layers and elastic properties on the nonlinear vibration are investigated. The presence of bending-extension coupling in antisymmetric plates yields a second power term in addition to a cubic nonlinear term in the governing differential equation of motion. However, for the symmetric plate case, this second term vanishes. The fundamental frequency of the analytical results are compared with that of the ABAQUS FEM analysis. For the nonlinear vibration of antisymmetric cross-ply composite plate, the results of reference are presented for comparison with these results.