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Design and analysis of composite material specimens exhibiting bend, torsion, and shear extension coupling

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Identifier	Thesis 1845
Author	Nace, Irena
Title	Design and analysis of composite material specimens exhibiting bend, torsion, and shear extension coupling
Publisher	Central Connecticut State University
Date	2005
Resource Type	Master's Thesis
Notes	The goal of this effort was the design and analysis of multiple composite material tension specimens, which when loaded only with an inplane load, exhibit bend, torsion, and shear extension coupling. The coupling effects distinguish composite materials from the classical isotropic materials, and the behavioral response of these materials is unexpected and somewhat odd. The American Society for Testing and Materials (ASTM) specifications provide detailed requirements and recommendations for composite tensile test specimens. These were used in conjunction with standard mold design procedures for the manufacture of the compression mold. A laminate analysis software package was used to verify the composite specimen design, analysis, response and load capabilities. The usable force resultant Nx range was found to be 0 to 2 x 106 N/m, a reflection of the intended test laboratory capability. The complete analyze was performed on S and E-glass/epoxy composite material specimen designs having three stacking sequences: 10-ply non-symmetric laminate [0/90/0/90/0/90/0/90/0/90] for bending extension coupling; 10-ply non-symmetric, but balanced laminate [45/-45/45/-45/45/-45/45/-45/45/-45] for torsion extension coupling; and 10-ply symmetric, but not balanced laminate with all layers at an angle θ = 300 [30/30/30/30/30/30/30/30/30/30] for shear extension coupling. The results of the three extension coupling deformations are presented. For both materials S and E-glass/epoxy the defining deformations found were δ = 4.17 mm, φ = 8o, and γ = 0.74o. The bending, torsion and shear extension coupling deformations appear to be visible, clearly visible, and possibly visible (certainly measurable) respectively. The maximum stress failure criterion was used to predict the failure. The results of this criterion are presented. The extension coupling deformations increase with decreasing the thickness of the laminate. The results of the thickness effect are presented. It is found that the extension coupling deformations directly increase with increasing the inplane load. The maximum inplane load permitted to use without laminate breakage is defined. It is also observed that the maximum strain failure criterion gives almost the same prediction of failure as the maximum stress failure criterion, and the Tsai-Wu criterion gives a different prediction of failure at lower load when interaction between two or more stresses are considered. The results of this study are also presented. Finally it is found that changing the layer orientations and keeping the rest of the laminate definition the same, can lead to a laminate, which exhibits different extension coupling deformation including combined effects such as bending-twisting coupling.
Subject	Composite materials -- Mechanical properties Composite materials -- Testing
Department	Department of Engineering Technology
Advisor	Baumann, Peter F.
Type	Text
Digital Format	application/pdf
Language	eng
OCLC number	713735051
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