Results 261 to 270 of about 143,763 (308)

Simple thickness modes for laminated composite materials

Journal of Sound and Vibration, 1972
The simple thickness modes for laminated media with layering both parallel and perpendicular to the plate-free surfaces are studied according to the “effective stiffness” theory and the results obtained are compared with results found from the effective modulus” theory.
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Delamination in Thickness Tapered Composite Laminates

Journal of Engineering Materials and Technology, 1993
The structural performance of thickness-tapered laminates has been investigated using an energy-based damage tolerance methodology. The geometry studied is a thin laminate with discontinuous internal plies and a through-width delamination embedded at the interface between continuous and discontinuous sublaminates.
B. R. Trethewey, J. W. Gillespie, D. J. Wilkins   +2 more
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Refined Theory for Thick Composite Plates

Journal of Engineering Mechanics, 1988
A refined theory for the bending of composite plates is developed, based on an assumed variation of the shear stresses through the thickness. The influence of transverse normal strain, transverse normal stress, and shear deformation is accounted for in the formulation. The development yields a bending‐extension coupling, yielding a tenth‐order boundary
George Z. Voyiadjis, Mohammed H. Baluch
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Z-PIN THROUGH-THICKNESS ENHANCEMENT OF A COMPOSITE LAMINATE WITH VARIABLE THICKNESS

2019
A multi-scale framework has been developed for the numerical modelling of composite laminates reinforced with z-pins and submitted to several delaminations of different mode-mixities.
Serra, Joël, Rui Melro, Antonio, Allegri, Giuliano, Hallett, Stephen R.   +3 more
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Vibrations of thick composite circular plates

Computers & Structures, 1992
Abstract The flexural vibration of thick composite circular plates is studied by the finite element method. An annular element based on a high-order plate theory is developed for the asymmetric motion. The present formulas can be simplified to obtain some other plate theories' formulas. Numerical results are presented for various plate constructions.
Hwang, J. R., Chen, Lien-Wen
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Dynamic Behavior of Thick Composite Beams

Journal of Reinforced Plastics and Composites, 1995
A numerical computation and experimental tests have been performed for the investigation of dynamic behavior of thick composite beams. The present finite element method can effectively evaluate transverse shear deformation by considering layerwise in-plane displacements. The natural frequencies and damping values were measured by fitting the frequency
Kyo-Nam Koo, In Lee
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Very Thick Walled Composite Shells

1993
In Chapter 13, methods of analysis are presented for very thick walled isotropic cylindrical bodies of h/R≤0.5 which were developed by Vinson [13.6, 13.7]. More recently, Waltz [23.1] extended those methods to the much more complicated case of a cylindrical shell body with h/R≤0.5 composed of a specially orthotropic composite material.
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Thick-walled wound fibrous-composite structures

Polymer Mechanics, 1976
Recent research on the high compliance of the modern fibrous composites in the transverse direction is reviewed. The following topics are examined in detail: deviations from the elastic-ring winding model, the effect of initial imperfections, methods of studying and taking into account the physical nonlinearity of the radial stress-strain dependence ...
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Localization of Ultrasound in Thick Composites

1990
The propagation of ultrasound in fiber-reinforced composites is controlled by the relative magnitudes of characteristic length variables. These length variables are the wavelength (Λ), the fiber diameter (a), the thicknesses of plies (h), and the overall thickness of the component (H).
Lu, Yichi, Achenbach, Jan
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Thickness Expansion Coefficients of Composite Laminates

Journal of Composite Materials, 1974
Fahmy and Ragai-Ellozy [1] have recently treated the problem of the thermal expansion coefficient in the thickness direction of a symmetric composite laminate. Unfortunately, however, an error has been made in their analysis. Specifically, Equation (1) of that work should take the form $${a_{3r}} = {a_T} - \frac{1}{{1 - {v_{12}}{v_{21}}}}\left ...
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