SYMPOSIA PAPER Published: 01 January 1996

Crack-Bridging Effects in Notch Fatigue of SCS-6/TIMETAL 21S Composite Laminates


Fatigue tests of middle-hole tension specimens of SCS-6/TIMETAL 21S composite (silicon-carbide fibers reinforcing a matrix of Ti-15Mo-2.6Nb-3Al-0.2Si alloy) were performed on three laminate architectures: unidirectional, cross ply, and quasi-isotropic. Specimens were tested over a range of stress levels, and fatigue damage was documented in situ by macrophotography and direct-current electric potential drop measurements. Typically, failure evolved by the formation of a few dominant cracks at the notch that propagated into the composite matrix and, in many instances, were substantially affected by unbroken fibers bridging the cracks. Fractographic and failure mode characterization revealed key differences in the effectiveness of crack bridging in the three laminates. A shear-lag crack-bridging model was shown to correlate crack growth data in the laminates based on an empirical value of fiber/matrix interfacial shear stress. Crack-bridging stress distributions were predicted using the shear lag model and verified by comparing the predicted crack opening displacement profiles with measurements made using a laser interferometric displacement gage system. Implications of the results are discussed with respect to the potential use of these materials in practical structural applications.

Author Information

Larsen, JM
Wright Laboratory, WL/MLLN, Wright-Patterson AFB, OH
Jira, JR
Wright Laboratory, WL/MLLN, Wright-Patterson AFB, OH
John, R
University of Dayton Research Institute, Dayton, OH
Ashbaugh, NE
University of Dayton Research Institute, Dayton, OH
Price: $25.00
Contact Sales
Reprints and Permissions
Reprints and copyright permissions can be requested through the
Copyright Clearance Center
Developed by Committee: D30
Pages: 114–136
DOI: 10.1520/STP18221S
ISBN-EB: 978-0-8031-5320-2
ISBN-13: 978-0-8031-2039-6