Moumita Roy

Graduation Semester and Year

2005

Language

English

Document Type

Thesis

Degree Name

Master of Science in Mechanical Engineering

Department

Mechanical and Aerospace Engineering

First Advisor

Wen Chan

Abstract

Predicting the strength of a given laminate has been extensively studied. There have been several fracture models proposed but still the immense tests of composite laminates are still needed. Different material systems or lay-ups exhibit different failure modes and failure mechanisms. This thesis focuses in investigation of the failure mechanism of the [±?/02]s and [02/±?]s laminates with a hole. ANSYS finite element models with and without a crack in vicinity of hole were developed to investigate the effect of the stress distribution due to the presence of the angle ply crack. The stress concentrations were obtained. It is found that The stress concentrations increases as d/w increases for a given ? in [±?/02]s and [02/±?]s laminates For a given d/w ratio, the stress concentrations increases as ply orientation,? increases The high stress concentrations on 0o ply occurs at the location where the ?-ply crack intercepts at the line perpendicular to the 0o ply Based upon the understanding the failure mechanism, a simple expression to estimate the strength of laminates with a hole is established. A strength model based upon the 0o ply load carrying capability is proposed. Prediction is a good agreement with the experimental results.

Disciplines

Aerospace Engineering | Engineering | Mechanical Engineering

Comments

Degree granted by The University of Texas at Arlington

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