Showing 13 results for Composite Laminate
Fareed Kaviani, Hamid Reza Mirdamadi,
Volume 12, Issue 6 (3-2013)
Abstract
In this paper, a novel four-variable refined theory of plate, called RPT, has been proposed for free vibration of composite laminated plates, using a hyperbolic sine function, for calculating out-of-plane shear strains. It is one of the properties of this theory that the boundary condition of zero shear stress is satisfied over upper layer and under lower layer of plate, with no reference to Timoshenko shape factor. In contrast to other higher-order shear deformation theories, in RPT theory, equations of motion are coupled dynamically only in inertial terms, while elastic energy terms are not coupled for the variables used. From this viewpoint, RPT theory is similar to classical plate theory (CLPT). Some of the objectives of this paper are the investigation of effect of influential parameters on fundamental frequency, such as modulus ratio, angle of plies, and plate length-to-thickness ratio. The results of this proposed version of RPT are compared and validated with those of first-order shear deformation theory (FSDT), higher-order shear deformation theory (HSDT), and the original version of RPT.
Alireza Keshmiri, Ali Ghaheri, Fathollah Taheri-Behrooz,
Volume 14, Issue 1 (4-2014)
Abstract
Buckling and vibration characteristics of thin symmetrically laminated elliptical composite plates under initial in-plane edge loads and resting on Winkler-type elastic foundation are presented based on the classical laminated plate theory. The governing equations are obtained from the variational approach and solved by the Ritz method. Extensive numerical data are provided for the first three natural frequencies as a function of in-plane load for various classical edge conditions (free, clamped and simply supported). Moreover, the effects of fiber orientation on the natural frequencies and buckling loads of laminated angle-ply plates with stacking sequence of [(β /-β / β /-β)]s, are studied for chosen foundation parameter. Also, selected deformation mode shapes are illustrated. The accuracy of calculations is checked by performing good convergence studies, and the correctness of results is established by comparison with the existing results in the literature as well as FEM data.
Rahmatollah Ghajar, Akbar Rassaf Sohi,
Volume 14, Issue 10 (1-2015)
Abstract
In this research, low velocity impact tests have been carried out on laminated composite plates to investigate the impactor shape and temperature effect on the dynamic behavior and material damage. The woven E glass/ epoxy laminates were manufactured. The studies have been done on plate with dimensions of 120 mm× 120 mm× 3 mm, impactor with 1.4 m/s incident velocity and 7 kg mass. Specimens have been impacted by using steel flat, hemispherical, ogival and conical impactors, all 12.7 mm in diameter. The specimens impacted by the conical impactor absorbed most energy because of local penetration. The flat impactor caused the highest peak force and lowest contact duration as expected. The force history of the impactor, projectile displacement and absorbed energy of different impactor shapes has been measured and compared with each other. The temperatures were in the range of room temperature to 150 °C. The parameters including maximum contact force, projectile displacement and the absorbed energy of different temperature have been investigated. Maximum contact force decreased with increasing of temperature, and deflection of impactor increased with increasing of temperature.
Mohammad Jafari, Behzad Moshiri,
Volume 14, Issue 15 (3-2015)
Abstract
In this paper, by expanding the Lekhnitiskii’s solution, the stress distribution around quasi-rectangular hole has been studied. Lekhnitiskii used complex variables analytic method for stress analysis of anisotropic plates with circular and elliptical hole. In order to extend the Lekhnitiskii’s analytical method for stress analysis of perforated symmetric laminates with non-circular holes, by means of conformal mapping, the area external to the hole can be represented by the area outside the unit circle. In this paper, try to study the effect of different parameters such as aspect ratio, stacking sequence, rotation angle of hole, bluntness and load angle on stress distribution around quasi-rectangular hole. The finite element method has been used to check the accuracy of analytical results. The analytical results are in good agreement with the numerical results. The results presented herein, indicated that the presented method can be used to determine accurately the stresses and stress concentration in composite plates with special shape cutouts .The results obtained clearly demonstrate the effect of these parameters on maximum stresses in perforated plates subjected to uni-axial tensile load. appropriate selection of bluntness and rotation angle of hole, can decrease stress concentration.
Ahmad Firouzian-Nejad, Saeed Ziaei-Rad, Masih Moor,
Volume 16, Issue 4 (6-2016)
Abstract
In this paper, thermal and vibration response of cross-ply bi-stable composite laminated plates were studied using semi-analytical, finite element and experimental method. In order to evaluate the semi-analytical and finite element results, a bi-stable composite plate was manufactured using a special procedure. Next, geometrical characteristics and displacement of different paths on the plate were measured experimentally at room temperature. In semi-analytical approach, the two stable states and the first natural frequency of cross-ply laminates are calculated based on Rayleigh–Ritz approach combined with Hamilton’s principle. In this study, a modified shape function was introduced that allows the curvatures to vary in both longitudinal and transverse directions. Using the modified shape function, the displacement of the plate in its stable configuration and the first natural frequency of the plate can be more accurately predicted in compared to the Hyer’s shape functions. The obtained results from the proposed shape function are in good agreement with the finite element and experimental data. The proposed shape functions can also be used in dynamic and vibration analysis to determine the snap-through load of the cross-ply laminates.
Ali Gholizade, Naeim Akbari Shah Khosravi, Reza Mohammadi, Mehdi Ahmadi Najafabadi, Hossein Heidary,
Volume 17, Issue 8 (10-2017)
Abstract
Nowadays fiber reinforcement composite are highly regarded, because of their proper mechanical properties and low weight. One of their main ways to assemble is drilling. Drilling causes to many failures such as: delamination, hole shrinkage, fibers pull-out and thermal failures. These failures reduce composite strength specially in fatigue loading. Using of carbon Nano tubes improve mechanical properties such as: hardness, strength, young module and stiffness. This investigation focuses on effect of added carbon Nano tubes Wt% on lifetime of glass/epoxy laminated composites under tensile - tensile fatigue loading. To main this purpose specimens whit different carbon Nano tubes Wt% have been made. They have been drilled by same condition. Then these specimens were subjected to tensile - tensile fatigue loading. AE sensors and microscopic camera were used to validate results. The results indicate that carbon Nano tubes Wt% increase, increase specimens fatigue life.
, Marzieh Hosseini,
Volume 18, Issue 2 (4-2018)
Abstract
In this research the influence of the striker shape on orthotropic composite plates for states, no damage (delamination) and damaged (delamination) are studied. In the analytical method, the spring mass system is used and new analytical model for flat and conical strikers are investigated. In the numerical method, the impact of different strikers on the composite laminate is simulated by using of finite element package (AnsysLs Dyna). These studies have been done on plates made of carbon and epoxy and the sheet thickness has been investigated in the size of 2, 4 and 6 mm. The striker mass is 3 g and its velocity for each thickness is different. To investigate the effects of the striker shape, three nose shapes spherical, conical and cylindrical with flat nose are modeled. The impacting time, the displacement time history and the maximum central deflection, and the contact force for all strikers are obtained and compared with each other. The results of analytical model are good agreement with numerical simulation. According to the results, when the delamination occurs, the maximum central deflection is more than once that damage dose not occurs. According to the results, the maximum central deflection of the flat striker on for both cases, with and without delamination, is less than the other strikers, conversely, the maximum contact force is more than the other strikers.
Mahdi Habibi, Jalal Yousefi, ,
Volume 18, Issue 4 (8-2018)
Abstract
Delamination is one of the major failure modes of the laminated composite material, which is responsible for the stiffness degradation of these materials. Hence, it is necessary to investigate this damage mechanism in these types of materials in order to distinguish their behaviors and their effects on the residual strength of the composite laminates. In this paper, a very capable procedure is proposed to assess delamination using Acoustic Emission (AE) method in composite laminates. Firstly, a novel procedure was established to decompose the fundamental Lamb wave modes in small size specimens. The damage mechanisms in End Notched Flexure (ENF) in woven and unidirectional specimens were then distinguished using Fuzzy Clustering Method (FCM). Subsequently, the crack-arrest phenomenon was inspected in each specimen. Next, experimental and Cohesive Zone Modeling (CZM) methods were done to characterize the delamination using ENF specimens. The results displayed how, it is possible to effectively reduce the effect of propagating media such as attenuation of AE signals using the new proposed procedure. In conclusion, the results of this research could lead to proficiently distinguishing different damages in laminated composite using AE Lamb-based technique.
Hamed Mahmoud Soltani, Mahsa Kharazi, Hamid Reza Ovesy,
Volume 18, Issue 5 (9-2018)
Abstract
In this study, the buckling and postbuckling behavior of composite laminates with piezoelectric layers subjected to compressive in-plane loading have been investigated. The effects of coupled electro-mechanical field on the postbuckling and bifurcation point in cross-ply and general lay-up sequences have been studied using layerwise theory (LWT). The LWT used in this study for analyzing the piezo-composite laminate is based on the assumptions of the first order shear deformation theory (FSDT). In order to obtain the equilibrium equations, the principle of minimum potential energy has been employed. The obtained nonlinear equilibrium equations have been solved using Newton-Raphson iterative algorithm. Furthermore, the three dimensional finite element analysis has been performed to examine the accuracy of the results obtained using the proposed method. The obtained analytical results are in good agreement with those achieved through the finite element analysis. Obtained results showed that, location of the piezoelectric layers have significant effect on the buckling and postbuckling behavior of the composite plates. Moreover, number of degrees of freedom which is used in proposed method are less than finite element method which, decreased the computational time cost.
M. Habibi, J. Yousefi, M. Ahmadi,
Volume 19, Issue 12 (12-2019)
Abstract
Delamination or interlayer cracking is one of the most important imperfections in composite materials. The existence of this defect in a structure reduces the strength and, as a result, disables the structure. To analyze the effective factors in interlayer separation, it is necessary to analyze the effective loading parameters. In this paper, the effect of the change in loading rate on the failure mechanism in I failure mode was analyzed using an acoustic emission for unidirectional samples made of glass fiber/epoxy resin. At first composite, samples were made according to standard and placed at different rates of displacement under loading. Force data, displacement and crack growth rate for different loading rates were used to calculate the exact strain energy release rate. In addition to the extensometer, the Dino camera was used. In this paper, a high-reliability method was proposed to evaluate the separation between the layered composites using acoustic emission method. By comparing mechanical data and acoustic emission signals, the mechanical behavior obtained for each loading rate was determined so that the mechanical behavior of the composite material varied with the change in loading rate. The results show that, with increasing loading rates, the resin lost its elastic properties, and the specimen exhibited a more rigid behavior and is quite rigorous so that the fracture failure process is changed. The failure processes and crack growth rate was validated by use of acoustic emission signals. There was good agreement between the fracture toughness of accretion of acoustic emission signals with the experimental values.
A. Firouzian-Nejad, M. Ghayour, S. Ziaei-Rad,
Volume 20, Issue 3 (2-2020)
Abstract
This study introduces a new lay-ups of bi-stable hybrid composite laminate (BHCL) which consists of 90° unidirectional composite laminas in the upper and lower layers and metallic strips distributed along with the middle layer of 0° unidirectional composite laminas in the middle layer. The static characteristics of the laminates were investigated using the finite element (FE) method and were experimentally validated. The two stable configurations of laminate have identical curvatures with opposite signs. The curvature direction of the proposed BHCLs does not change during snap-through between stable states. This feature will give the engineers more freedom to design morphing structures with desired specifications. The effect of the width, thickness, and material properties of the strips and laminate side length on the static characteristics of the laminate were numerically investigated using the finite element method through Abaqus software. Several BHCLs with different materials, lay-up and dimension were fabricated for verification of the results. The curvatures, out of plane displacement, and the static snap-through load of the laminates were determined experimentally and compared with the results of the finite element method. A good qualitative and quantitative agreement was observed between the FE and the experimental results. The results show that it is possible to adjust residual curvature and load-carrying capability by changing the width, thickness, and material of the strips and laminate geometry.
M. Pakravan, M. Farahani,
Volume 20, Issue 4 (4-2020)
Abstract
Nowadays, the use of a non-contact digital imaging system for non-destructive testing on composite materials has received much attention because of its advantages. In this research, the shape, position and area of the breakdown region in glass/epoxy samples with blind holes and different depths under tensile loading have been investigated using a non-contact digital imaging system. Specimens with a 10 mm diameter blind, depths of 0.5, 1 and 1.5 mm, and an average thickness of 4 mm have been subjected to the tensile loading. Lateral strain contours for all three samples have been obtained at different loads. By increasing the lateral strain loading, it focuses on an area on the surface of each specimen that corresponds to the position of the blind hole. Then the lateral strain is measured separately in length and width for each specimen. Increasing the amount of loading and the depth of the breakdown have resulted in greater strain concentration in the breakdown area as well as increasing the accuracy of the digital images correlation system. The position, shape, area, and diameter of the blind hole measured by digital image correlation method have been compared with real values, which considering the acceptable consistency of the results of the digital image correlation method with the features of each sample, It can be used as an efficient method for detecting and evaluating failures in composite structures.
Mehrdad Ghadami, Rahmatollah Ghajar,
Volume 22, Issue 12 (12-2022)
Abstract
Once a composite laminate is subjected to quasi-static tensile or fatigue loading, some damage modes initiate and propagate in the laminate. The first damage mode is the matrix crack that forms in the layers with an angle to the loading direction. Although not leading to breakage, these cracks reduce the equivalent mechanical properties of the composite laminate. In this paper, a new nonlinear analytical model is presented and used to predict the stiffness degradation of the cross-ply composite laminates. For this purpose, a new third-order polynomial function is proposed as the Helmholtz free energy of the composite, and the appropriate equations are derived. A microscopic experimental test is designed and accompanied by the analytical model to investigate the damage progression in a glass/epoxy cross-ply laminate. Also, finite-element micromechanical models with periodic boundary conditions (PBC) are proposed and used to determine the damage constants. The model is validated against the 3D micromechanical models and the quasi-static uniaxial loading-unloading experimental tests. The validation shows a very good agreement between the model and the experiments.
