Fatigue Damage in Cross-Ply Titanium Metal Matrix Composites Containing Center Holes

The development of fatigue damage in four [0/90]s SCS-6/Ti-15-3 laminates containing center holes was investigated. A methodology to predict damage initiation based on an effective strain parameter was used to determine the stress levels and the number of cycles required for matrix crack initiation....

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Bibliographic Details
Published in:Journal of engineering materials and technology 1993-10, Vol.115 (4), p.404-410
Main Authors: Bakuckas, J. G, Johnson, W. S, Bigelow, C. A
Format: Article
Language:English
Subjects:
360603 - Materials- Properties
ALLOYS
Applied sciences
CARBIDES
CARBON COMPOUNDS
COMPOSITE MATERIALS
CRACK PROPAGATION
DAMAGE
Exact sciences and technology
FAILURES
FATIGUE
MATERIALS
MATERIALS SCIENCE
MECHANICAL PROPERTIES
Mechanical properties and methods of testing. Rheology. Fracture mechanics. Tribology
Metals. Metallurgy
SILICON CARBIDES
SILICON COMPOUNDS
TITANIUM ALLOYS
TITANIUM BASE ALLOYS
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Summary:The development of fatigue damage in four [0/90]s SCS-6/Ti-15-3 laminates containing center holes was investigated. A methodology to predict damage initiation based on an effective strain parameter was used to determine the stress levels and the number of cycles required for matrix crack initiation. Damage progression was monitored at various stages of fatigue loading. In general, a saturated state of damage consisting of matrix cracks and fiber-matrix debonding was obtained which reduced the composite modulus. Matrix cracks were bridged by the 0° fibers. The fatigue limit (stress causing catastrophic fracture of the laminates) was also determined. The static and post-fatigue residual strengths were accurately predicted using a three dimensional elastic-plastic finite element analysis. The matrix damage that occurred during fatigue loading significantly reduced the notched strength.
ISSN:0094-4289
1528-8889
DOI:10.1115/1.2904238