Graduation Semester and Year

2008

Language

English

Document Type

Thesis

Degree Name

Master of Science in Aerospace Engineering

Department

Mechanical and Aerospace Engineering

First Advisor

Wen Chan

Abstract

Unlike isotropic material, the stress distribution of laminate with a hole varies with its size, its material properties and fiber orientations of each layer. Moreover, presence of a hole in the neighborhood of another hole may also affect their stress distribution, too. The major objective of this study is to determine stress distribution of finite width laminated composite having multiple holes. The effect of stress concentration due to presence of holes in each angle ply of laminated composite is a focus of this study. Three dimensional finite element models are developed to determine the stress distribution in laminate using commercial software package ANSYS 10.0 classic. The material used for laminated composite is T300/977-2 grphite/epoxy with [03/±45/90]s laminate layup. The stress distribution of composite laminate with single, two and three holes is investigated. The effect of proximity of single hole to laminate edge is also discussed. The stress concentration for "two holes oriented in-line with load" and "two holes oriented side by side transverse to load" are discussed. The effects of "hole size ratio" and "edge distance between two holes" on stress distribution are also investigated. The patterns of three holes placed at three vertices of a triangle with different edge distance between holes are also been included in this study. The maximum stress concentration found at the point on hole periphery where fibers are tangent to the hole. The patterns of the hole orientation and holes size ratio as well as the edge distance between holes play important role on the magnitude of stress concentration of composite laminates.

Disciplines

Aerospace Engineering | Engineering | Mechanical Engineering

Comments

Degree granted by The University of Texas at Arlington

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