Fatigue behavior and failure mechanisms of centrally notched (0)8 and ((0/90)2)(S) silicon-carbide-reinforced aluminosilicate glass (Final report). Master's thesis

Technical Report · Sun Dec 01 04:00:00 EST 1991

OSTI ID:5711580

Moschelle, W R

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. (0/90)(2)(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.

• Research Organization: Air Force Inst. of Tech., Wright-Patterson AFB, OH (United States). School of Engineering
• OSTI ID: 5711580
• Report Number(s): AD-A-243879/4/XAB
• Country of Publication: United States
• Language: English

Related Subjects

36 MATERIALS SCIENCE
360603* -- Materials-- Properties
AEROSPACE INDUSTRY
CARBIDES
CARBON COMPOUNDS
COMPOSITE MATERIALS
CRACKS
DAMAGE
FAILURES
FATIGUE
GLASS
INDUSTRY
LAYERS
MATERIALS
MATHEMATICAL MODELS
MATRIX MATERIALS
MECHANICAL PROPERTIES
NOTCHES
REINFORCED MATERIALS
SILICON CARBIDES
SILICON COMPOUNDS
TENSILE PROPERTIES