Journal ArticleDOI
Interlaminar Stresses in Composite Laminates Under Uniform Axial Extension
R. Byron Pipes,N. J. Pagano +1 more
TLDR
In this article, the response of a finite-width composite laminate under uniform axial strain is treated through the application of classical elasticity theory, and finite-difference solution techniques are employed to obtain solutions for stresses and displacements throughout the region.Abstract:
The response of a finite-width composite laminate under uniform axial strain is treated through the application of classical elasticity theory. Finite-difference solution techniques are employed to obtain solutions for stresses and displacements throughout the region. Results for material properties typical of a high modulus graphite-epoxy composite material system are presented which explain the mechanism of shear transfer within a symmetric laminate. In addition, results of this work are compared to those given in a recent approximate formulation.read more
Citations
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Dissertation
Interlaminar stresses at straight free edges of composite laminates
TL;DR: Thesis (M.S.) as discussed by the authors, Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics; and, M.S., MIT, Dept of Mechanical Engineering, 1985.
Journal ArticleDOI
Use of carbon fiber-reinforced plastics in aircraft construction
TL;DR: In this article, a unified finite element method has been developed for calculating the stress-strain state of aircraft control surfaces made of composites and has been used to solve the problem of finding the optimum distribution of material (thickness and arrangement of the laminations) consistent with satisfaction of the static and acoustic strength requirements and possible technological constraints.
Journal ArticleDOI
Analysis of multi-layered microelectronic packaging under uniformly distributed loading
Yujun Wen,Cemal Basaran +1 more
TL;DR: An analytical model for stress analysis of multi-layered stacks, which is based on an extension of Valisetty's model (Bending of Beams, Plates and Laminates: Refined Theories and Comparative Studies, Ph.D. thesis, Georgia Institute of Technology, Atlanta, March 1983), is proposed in this article.
Journal ArticleDOI
Influence of stacking sequence and interlaminar layer on stress singularities at free edge of composite laminates
TL;DR: In this article, the singularity in the state of stress existing at the free edges of plane composite laminates with resin interlaminar layer was studied by means of a F.E. approach, founded on a method able to determine the free edge state without aprioristical hypotheses about the presence of a singularity.
Book ChapterDOI
An Energy Release Rate Approach for Free-edge Delamination Problem in Composite Laminates
Kyohei Kondo,Takahira Aoki +1 more
TL;DR: In this paper, the saturated value of energy release rate is used as a measure to predict the occurrence of delamination which has yielded good agreement with observations on tension-tension and compression compression fatigue tests conducted on carbon-epoxy composite laminates.
References
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Journal ArticleDOI
Theory of Elasticity of an Anisotropic Elastic Body
Journal ArticleDOI
Edge-Bonded Dissimilar Orthogonal Elastic Wedges Under Normal and Shear Loading
Journal ArticleDOI
Bending and Stretching of Certain Types of Heterogeneous Aeolotropic Elastic Plates
Eric Reissner,Y. Stavsky +1 more
Journal ArticleDOI
Interlaminar Shear in Laminated Composites Under Generalized Plane Stress
A.H. Puppo,H.A. Evensen +1 more
TL;DR: In this article, an analysis of interlaminar shear stresses is performed for a laminate under generalized plane stresses, where the laminate is modeled as a set of anisotropic layers separated by isotropic adhesive layers.
Related Papers (5)
Some New Results on Edge Effect in Symmetric Composite Laminates
A.S.D. Wang,Frank W. Crossman +1 more
Boundary-Layer Effects in Composite Laminates: Part 1—Free-Edge Stress Singularities
Su Su Wang,I. Choi +1 more
Interlaminar Shear in Laminated Composites Under Generalized Plane Stress
A.H. Puppo,H.A. Evensen +1 more