Date of Award

12-1992

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Shankar Mall, PhD

Abstract

Quasi-Static tensile and compressive testing was performed on a unidirectional titanium matrix composite. The specific material was SCS-9/β 21S. The initial tensile and compressive modulus for both laminates was the same. The ninety degree laminate had a tensile and compressive modulus of 115.89 GPa. The zero degree laminate had a tensile and compressive modulus of 197.51 GPa. The ninety degree laminate exhibited a three stage stress/strain response in tension. The first stage is completely linearly elastic, however, partial debonding of the fiber from the matrix was observed. This partial debased did not effect the stress/strain response. The second stage is due to the complete debond of the fiber from the matrix. The ninety degree laminate in compression had a two stage stress/strain response, and the zero degree laminate had a two stage stress/strain response in tension and compression. Plasticity and damage were the main causes of deformation. Plasticity involved deformation of the matrix between the fibers and Poisson's contraction of the matrix from the fibers. Damage involved fiber matrix d matrix cracking and fiber cracking. All of these mechanisms were present, and they were related to the appropriate stress/strain characteristics.

AFIT Designator

AFIT-GAE-ENY-92D-07

DTIC Accession Number

ADA258828

Comments

The author's Vita page is omitted.

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