Failure Behavior of Two Parallel Pinned/Bolted Composite Joints

2011 ◽  
Vol 27 (1) ◽  
pp. 121-127
Author(s):  
M. Pakdil ◽  
F. Sen ◽  
A. Cakan
Keyword(s):  
Glass Fibers ◽  
Laminated Composite ◽  
Composite Plates ◽  
Diameter Ratio ◽  
Laminated Plates ◽  
Hole Diameter ◽  
Failure Behavior ◽  
Geometrical Parameters ◽  
Composite Joints ◽  
Laminated Composite Plates

ABSTRACTIn this study, the failure behavior of two parallel pinned/bolted composite joints was investigated, experimentally. The laminated composite plates were produced from glass fibers and epoxy matrix. During the tests, various joint geometries and ply orientations were considered to decide the optimum joint geometry and suitable stacking sequence of the laminated composite plates for two parallel pinned/bolted joints. For these reasons, the distance from the free edge of the plate to hole diameter ratio (E/D) was changed from 1 to 5, the distance between two parallel holes to hole diameter ratio (K/D) was selected as 2 and 5, the distance from the lateral edge of the plate to hole diameter ratio (N/D) was taken as 2 and 3. The laminated plates were composed from 8 laminas to stuck onto together with three different orientations as [0°2 / 30°2]s, [0°2 / 45°2]s and [0°2 / 60°2]s. The experiments involved both pinned and bolted joint. Experimental results indicate that failure behaviors of pinned/bolted composite joints are strictly influenced from both orientations of laminated plates and geometrical parameters.

Investigation on Interlaminar Shear Stresses in Laminated Composite Plates under Thermal and Mechanical Loading

2014 ◽  
Vol 592-594 ◽  
pp. 451-455
Author(s):  
Nagaraj Murugesan ◽  
Vasudevan Rajamohan
Keyword(s):  
Finite Element ◽  
Thermal Environment ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Plates ◽  
Shear Stresses ◽  
Laminated Composite Plates ◽  
Interlaminar Stresses ◽  
Composite Laminated Plates ◽  
Interlaminar Shear

In this study the combined effect of thermal environment and mechanical loadings on the interlaminar shear stresses of both moderately thin and thick composite laminated plates are numerically analyzed. The finite element modeling of laminated composite plates and analysis of interlaminar stresses are performed using the commercially available software package MSC NASTRAN/PATRAN. The validity of the present finite element analysis is demonstrated by comparing the interlaminar stresses developed due to mechanical loadings derived using the present FEM with those of available literature. Various parametric studies are also performed to investigate the effect of thermal environment on interlaminar stresses generated in asymmetric cross-ply composite laminated plates of different length to thickness ratios (L/H) and boundary conditions with identical mechanical loadings. It is observed that the elevated thermal environment under identical mechanical loading lead to higher interlaminar shear stresses varying with length to depth ratio and boundary conditions in asymmetric cross-ply laminated composite plates.

scholarly journals Nonlinear Free Vibration for Viscoelastic Moderately Thick Laminated Composite Plates with Damage Evolution

2010 ◽  
Vol 2010 ◽  
pp. 1-15 ◽  
Author(s):  
Y. F. Zheng ◽  
L. Q. Deng
Keyword(s):  
Free Vibration ◽  
Transverse Shear ◽  
Superposition Principle ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Plates ◽  
Damage Effect ◽  
Laminated Composite Plates ◽  
Nonlinear Free Vibration ◽  
The Galerkin Method

The nonlinear free vibration for viscoelastic cross-ply moderately thick laminated composite plates under considering transverse shear deformation and damage effect is investigated. Based on the Timoshenko-Mindlin theory, strain-equivalence hypothesis, and Boltzmann superposition principle, the nonlinear free vibration governing equations for viscoelastic moderately thick laminated plates with damage are established and solved by the Galerkin method, Simpson integration, Newton-Cotes, Newmark, and iterative methods. In the numerical results, the effects of transverse shear, material viscoelasticity, span-thickness ratio, aspect ratio, and damage effect on the nonlinear free vibrating frequency of the viscoelastic cross-ply moderately thick laminated plates are discussed.

The Effects of Ply Angle of Laminated Composite Plates on Wind Induced Vibration

2012 ◽  
Vol 591-593 ◽  
pp. 1978-1981
Author(s):  
Jin Qiang Li ◽  
Yoshihiro Narita
Keyword(s):  
Ritz Method ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Plates ◽  
Wind Pressure ◽  
Laminated Composite Plates ◽  
Flow Induced Vibration ◽  
Analytical Methodology ◽  
Minimum Displacement ◽  
Wind Induced Vibration

This paper presents an analysis on the effect of ply angle for laminated composite plates on wind induced vibration. With Hamilton’s principle and the Rayleigh-Ritz method, the equation of motion for the wind induced vibration is derived. The displacements in time domain and the mean-square value of the transverse response under wind pressure are studied for laminated plates with different ply angles. From the numerically simulation results it is seen that the ply angle of the laminated plate can significantly affect the wind induced vibration. For different rectangle plate the optimal ply angles of minimum displacement is different. The analytical methodology in this paper can be expanded to other kinds of random vibration such as water flow induced vibration.

Failure behavior of laminated composite plates with two serial pin-loaded holes

2008 ◽  
Vol 82 (2) ◽  
pp. 225-234 ◽  
Author(s):  
Ramazan Karakuzu ◽  
Cihan Rıza Çalışkan ◽  
Mehmet Aktaş ◽  
Bülent Murat İçten
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Failure Behavior ◽  
Laminated Composite Plates

Fiber Orientation Angles Optimization for Maximum Fundamental Frequency of Laminated Composite Plates by the Genetic Algorithm and Meshless Method

2014 ◽  
Vol 709 ◽  
pp. 130-134
Author(s):  
Feng Wang ◽  
Wei Ping Zhao ◽  
Song Xiang
Keyword(s):  
Genetic Algorithm ◽  
Fundamental Frequency ◽  
Fiber Orientation ◽  
Meshless Method ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Plates ◽  
Laminated Composite Plates ◽  
Fundamental Frequencies ◽  
Design Variables

Fiber orientation angles optimization is carried out for maximum fundamental frequency of clamped laminated composite plates using the genetic algorithm. The meshless method is utilized to calculate the fundamental frequency of clamped laminated composite plates. In the present paper, the maximum fundamental frequency is an objective function; design variables are a set of fiber orientation angles in the layers. The examples of square laminated plates are considered. The results for the optimal fiber orientation angles and the maximum fundamental frequencies of the 2-layer plates are presented.

Analysis of Laminated Plates Subjected to Mechanical and Hygrothermal Environmental Loads Using Fifth-Order Shear and Normal Deformation Theory

2020 ◽  
Vol 12 (03) ◽  
pp. 2050028 ◽  
Author(s):  
Nitin S. Naik ◽  
Atteshamuddin S. Sayyad
Keyword(s):  
Deformation Theory ◽  
Shape Function ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Plates ◽  
Laminated Composite Plates ◽  
Normal Deformation ◽  
Polynomial Type ◽  
Fifth Order ◽  
First Time

Bending analysis of laminated composite plates subjected to mechanical and hygrothermal environmental loading is presented in this paper using fifth-order shear and normal deformation theory (FOSNDT). This theory uses polynomial-type shape function in the displacement field up to fifth-order. This theory considers the effect of transverse normal deformations ([Formula: see text]). Simply supported laminated composite and sandwich plates are analyzed using Navier’s solution techniques. The results obtained using this theory are compared with the results available in the literature wherever possible. However, many results are presented for the first time in this paper.

Wave-based impact localization on laminated composite plates using a coarse network of sensors

2019 ◽  
Vol 18 (5-6) ◽  
pp. 2040-2055
Author(s):  
Theodosis C Theodosiou ◽  
Christoforos S Rekatsinas ◽  
Christos V Nastos ◽  
Dimitris A Saravanos
Keyword(s):  
Laminated Composite ◽  
Composite Plates ◽  
Wave Dispersion ◽  
Laminated Plates ◽  
Accurate Estimation ◽  
Frequency Content ◽  
Laminated Composite Plates ◽  
Impact Site ◽  
The Impact ◽  
Impact Localization

This article demonstrates a methodology for the detection of foreign object impact locations on laminated composite plates using a low number of sensors. The proposed approach exploits the wave-dominated transient response of the target structure and addresses the challenges induced by the non-uniform wave propagation due to the anisotropy of composite plates on the impact localization. Captured sensor signals are processed and their frequency content is identified. Semi-analytical wave dispersion models and time-domain spectral finite element impact models encompassing the effects of laminate anisotropy on wave dispersion characteristics are employed to extract the wave velocity from their frequency content. The method for localizing the impact site is formulated as an optimization problem and involves signal correlation from different sensors, refinement of the candidate locations, and finally accurate estimation of the impact site. Numerical and experimental validations of the developed method are presented for low-velocity impacts on glass/epoxy laminated plates.

Failure Response of Two Serial Bolted Joints in Composite Laminates

2011 ◽  
Vol 27 (3) ◽  
pp. 293-307 ◽  
Author(s):  
F. Sen ◽  
O. Sayman
Keyword(s):  
Composite Laminates ◽  
Glass Fibers ◽  
Diameter Ratio ◽  
Hole Diameter ◽  
Bolted Joints ◽  
Geometrical Parameters ◽  
Material Parameters ◽  
Joint Geometry ◽  
Parametric Studies ◽  
Plate Width

ABSTRACTIn this study, the failure response of two serial bolted joints in composite laminates was investigated. The composite material was consisted of epoxy matrix and glass fibers. To find out the effects of joint geometry and stacking sequences on the failure response, parametric studies were performed experimentally. Three different geometrical parameters that were the edge distance-to-hole diameter ratio (E/D), plate width-to-hole diameter ratio (W/D) and the distance between two serial holes-to-hole diameter ratio (K/D) were investigated. Hence, E/D, W/D and K/D ratios were considered from 1 to 5, 2 to 5 and 3 to 5, respectively. In addition, the failure tests were carried out for a range of preload moments as 2, 3, 4, 5 Nm and without any preload moments as 0Nm. Tested composite laminates were oriented two different stacking sequences as [0°]8 and [0°/0°/90°/90°]s. Experimental results point out that failure response of two serial bolted composite joints are firmly effected from material parameters, geometrical parameters and the magnitudes of applied preload moments.

Application of the Method of Reverberation Ray Matrix to the Early Short Time Transient Responses of Stiffened Laminated Composite Plates

2012 ◽  
Vol 79 (4) ◽  
Author(s):  
Feng-Ming Li ◽  
Chun-Chuan Liu ◽  
Sheng Shen ◽  
Wen-Hu Huang
Keyword(s):  
Dynamic Models ◽  
Shear Deformation Theory ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Plates ◽  
Laminated Plate ◽  
Laminated Composite Plates ◽  
Transient Responses ◽  
Transient Wave ◽  
Short Time

The method of reverberation ray matrix (MRRM) is extended to research the transient wave propagation and early short time transient responses of the stiffened laminated composite plates subjected to impact loads. The rib-stiffened laminated plates are modeled as the coupling systems in which the flexural motion for the laminated plate is considered, and the flexural and torsional motions are taken into account for the laminated stiffeners, which are modeled as the beams. The dynamic models of the laminated plates and beams in the Laplace phase space are established based on the first order shear deformation theory (FSDT). The reverberation ray matrix is determined by the continuous and boundary conditions of the stiffened laminated plate. The transient response corresponding to each ray group is calculated by the FFT algorithm. From the numerical results, it is seen that the early short time transient accelerations of the stiffened laminated plates are very large, while the early short time transient displacements are very small. Furthermore, the influences of the stiffeners and different impulse signals on the early short time transient responses of the stiffened laminated plates are also studied.

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