Accession Number:

ADA243879

Title:

Fatigue Behavior and Failure Mechanisms of Centrally Notched (0)8 and (0/90)2(S) Silicon Carbide Reinforced Aluminosilicate Glass

Descriptive Note:

Final rept.

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1991-12-01

Pagination or Media Count:

164.0

Abstract:

Unidirectional and bidirectional notched laminates of silicon carbides1723 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 08 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. 0902S 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.

Subject Categories:

  • Laminates and Composite Materials

Distribution Statement:

APPROVED FOR PUBLIC RELEASE