Fatigue Behavior and Failure Mechanisms of Centrally Notched [0]₈ and [0/90₂]_s Silicon Carbide Reinforced Aluminosilicate Glass

Author

William R. Moschelle

Date of Award

12-1991

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Shankar Mall, PhD

Abstract

Unidirectional and bidirectional notched laminates of silicon carbides/1723 were fatigue tested under tensile-tensile loading with a load ratio of 0.1. The notch, a hole, was determined to have a significant effect on [0]₈ specimens. Matrix cracking developed near the theoretical maximum stress concentration points on the hole propagating parallel to the fibers, in the load direction, followed by fiber breakage. [0/90₂]_s specimens were found to be notched insensitive. Damage modes for this lay-up were transverse ply matrix cracking, delamination and fiber breakage in the longitudinal plies which led to specimen failure. Several existing analytical models were then applied to these laminates to predict fatigue life.

AFIT Designator

AFIT-GAE-ENY-91D-19

DTIC Accession Number

ADA243879

Comments

The author's Vita page is omitted.

Plain-text title form: Fatigue Behavior and Failure Mechanisms of Centrally Notched (0)8 and (0/90)2(S) Silicon Carbide Reinforced Aluminosilicate Glass

Recommended Citation

Moschelle, William R., "Fatigue Behavior and Failure Mechanisms of Centrally Notched [0]₈ and [0/90₂]_s Silicon Carbide Reinforced Aluminosilicate Glass" (1991). Theses and Dissertations. 7470.
https://scholar.afit.edu/etd/7470