SYMPOSIA PAPER Published: 01 January 1996

Damage Accumulation in Titanium Matrix Composites Under Generic Hypersonic Vehicle Flight Simulation and Sustained Loads


The damage accumulation behavior of a [0/90]2s laminate made of Ti-15V-3Cr-3Al-3Sn (Ti-15-3) reinforced with continuous silicon-carbide fibers (SCS-6) subjected to a simulated generic hypersonic flight profile, portions of the flight profile, and sustained loads was evaluated experimentally. Portions of the flight profile were used separately to isolate combinations of load and time at temperature that influenced the fatigue behavior of the composite. Sustained load tests were also conducted and the results were compared with the fatigue results under the flight profile and its portions. The test results indicated that the fatigue strength of this materials system is considerably reduced by a combination of load and time at temperature.

Author Information

Johnson, WS
School of Materials Science and Engineering, Georgia Tech, Atlanta, GA
Mirdamadi, M
General Electric Co., Power Generation System, Schenectady, NY
Bakuckas, JG
Galaxy Scientific Corp., Pleasantville, NJ
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Developed by Committee: E08
Pages: 252–265
DOI: 10.1520/STP16457S
ISBN-EB: 978-0-8031-5325-7
ISBN-13: 978-0-8031-2001-3