Text icon  Fatigue damage in cross-ply titanium metal matrix composites containing center holes

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Description: This resource is a report from NASA about fatigue damage in cross ply titanium metal matrix composites. The development of fatigue damage in (0/90) sub SCS-6/TI-15-3 laminates containing center holes was studied. Stress levels required for crack initiation in the matrix were predicted using an effective strain parameter and compared to experimental results. 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 deg 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.
Keywords: metal • matrix • composite • failure • NASA • Ti • titanium • silicon • carbide • crack • cross-ply • laminate • fibre bridging • FB • stress • modulus reduction • fibre-matrix debonding • report
Categories: Science approaches > Deformation & failure > Fracture
Science approaches > Deformation & failure > Fatigue
Materials > Hybrids > Composites > Metal matrix
Materials > Metals & alloys > Titanium & alloys
Created by: J. G. Bakuckas, Jr, NRC, Langley Research Center, NASA
W. S. Johnson, MEMB, Langley Research Center, NASA
License: This resource is released under the Creative Commons Public Domain Mark license ( ).
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Date created: 19 January 1992
Date added: 06 April 2011
Resource ID: 3622