Physical Ultrasonics of Composites

Author(s):  
Dale Chimenti ◽  
Stanislav Rokhlin ◽  
Peter Nagy

Physical Ultrasonics of Composites is a rigorous introduction to the characterization of composite materials by means of ultrasonic waves. Composites are treated here not simply as uniform media, but as inhomogeneous layered anisotropic media with internal structure characteristic of composite laminates. The objective here is to concentrate on exposing the singular behavior of ultrasonic waves as they interact with layered, anisotropic materials, materials which incorporate those structural elements typical of composite laminates. This book provides a synergistic description of both modeling and experimental methods in addressing wave propagation phenomena and composite property measurements. After a brief review of basic composite mechanics, a thorough treatment of ultrasonics in anisotropic media is presented, along with composite characterization methods. The interaction of ultrasonic waves at interfaces of anisotropic materials is discussed, as are guided waves in composite plates and rods. Waves in layered media are developed from the standpoint of the "Stiffness Matrix", a major advance over the conventional, potentially unstable Transfer Matrix approach. Laminated plates are treated both with the stiffness matrix and using Floquet analysis. The important influence on the received electronic signals in ultrasonic materials characterization from transducer geometry and placement are carefully exposed in a dedicated chapter. Ultrasonic wave interactions are especially susceptible to such influences because ultrasonic transducers are seldom more than a dozen or so wavelengths in diameter. The book ends with a chapter devoted to the emerging field of air-coupled ultrasonics. This new technology has come of age with the development of purpose-built transducers and electronics and is finding ever wider applications, particularly in the characterization of composite laminates.

2013 ◽  
Vol 712-715 ◽  
pp. 1075-1079
Author(s):  
Zai Ling Cheng ◽  
Cheng Shuang Han ◽  
Hong Mei Zhang

The development of computer technology has provided advanced methods for the analysis of complex mechanics problems. Along with the enhancement of computer speed, the computational time used in a finite element analysis is reduced significantly. The main work in a pre-bucking finite element analysis will concentrate on structuring the analytical model and the software model. A normalized factor of the normalized determinant DET of stiffness matrix is defined in this article.The finite element analysis model used in the pre-bucking analysis of laminated composite plates and shells is presented based on the characteristic of the DET. An algorithm for controlling computational procedure and determining critical load is also presented. Numerical examples are given to validate the proposed method and satisfactory results are obtained.


From past two-three decades there has been a gradual shift from monolithic to composite materials in order to meet the increasing demand for lighter, high performance, environment friendly, corrosion and wear resistant materials. Composite materials are majorly used in massive production like boats, automotive and air craft Industry etc. in order to improve hardness and impact strength. The manufacturing of hybrid composite laminates is difficult to handle by traditional methods and gives size restrictions, wetting, poor surface finish, more number of moulding required for manufacturing. The Hand lay-up chosen as the fabrication technique when product needs smooth finish slight variations in thickness and number of moldings required is less. The moulding made from materials like plastics, wood, clay, plaster or plywood depending on the availability. Hand lay-up technique has been adopted to manufacture the hybrid composite laminated plate (sawdust with 1%, 2% and 3% variation) and impact strength and hardness is to be calculated.


2006 ◽  
Vol 306-308 ◽  
pp. 375-380
Author(s):  
Heung Soo Kim ◽  
Seung Bok Choi ◽  
Jae Hwan Kim

A dynamic analysis method has been developed to investigate and characterize the effect due to the presence of discrete single and multiple delaminations of composite laminated structures. The Fermi-Dirac distribution function is combined with an improved layerwise laminate theory to model a smooth transition in the displacement and the strain fields of the delaminated interfaces. In modeling piezoelectric composite plates, a coupled piezoelectric-mechanical formulation is used in the development of the constitutive equations. Based on the developed model, the effects of discrete delaminations are quantified by comparing transient responses of composite plates and piezoelectric sensor outputs.


1982 ◽  
Vol 49 (4) ◽  
pp. 740-746 ◽  
Author(s):  
Y. A. Bahei-El-Din ◽  
G. J. Dvorak

Elastic-plastic behavior of symmetric metal-matrix composite laminates is analyzed for the case of in-plane mechanical loading. The overall response of the laminate at each instant is derived from the elastic-plastic deformation of the individual fibrous layers, and from their mutual constraints. Constitutive equations of the laminated plates are presented in terms of initial yield conditions, hardening rules, and instantaneous compliances. Local stresses, hardening parameters, and strains are found in each lamina and in the fiber and matrix phases within each lamina. Specific results are obtained with the continuum model of elastic-plastic fibrous composites [1] which has been recently developed by the authors. Comparisons of analytical results with experimental measurements are made for certain laminated plates.


2015 ◽  
Vol 24 (1) ◽  
pp. 096369351502400 ◽  
Author(s):  
Mohammad Amin Torabizadeh

An analytical and numerical solution for general laminated composite plates under mechanical loading is presented based on different lamination plate theories (CLPT and FSDT). General lamination was evaluated by assumption of cross-ply and angle-ply laminated plates. In order to this, Navier-type method and simply supported boundary conditions for rectangular laminates are applied. As a verification method, a finite element code using ANS YS is also developed. Effects of lamination scheme, axial load direction, modulus ratio, plate aspect ratio and lamination angle on critical buckling loads of laminated composite are also investigated and good agreement is found between evaluated results and those available in open literature.


2017 ◽  
Vol 24 (6) ◽  
pp. 937-949
Author(s):  
Jie Chen ◽  
Hai Wang ◽  
Yingchun Zhang ◽  
Lihua Zhan

AbstractA three-dimensional (3D) semi-analytical model is developed by introducing meshfree local radial point interpolation method into a Hamilton system to analyze the mechanical and thermal buckling behavior of rectangular laminated plates with embedded delaminations. A modified Hamiltonian function for mechanical and thermal buckling analysis of rectangular laminated composite plates subjected to in-plane axial compressive or thermal loads is proposed. The final governing equation is deduced with the transfer matrix technique and a spring layer model based on the modified Hellinger-Reissner variational principle. One of the main superiorities of the present model is that the scale of final governing equation, which involves only the so-called state variables at the top and bottom surfaces, is insensitive to the thickness and the number of layers of composite laminates. Several relevant numerical examples are carried out to validate the present model, and the present results are in good agreement with pre-existing results.


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