Characterization of Fatigue Behavior in Cross-Ply Laminate of SCS-6/Ti-15-3 Metal Matrix Composite at Elevated Temperature

[+] Author and Article Information
S. Mall, B. Portner

Department of Aeronautics and Astronautics, Air Force Institute of Technology, Wright-Patterson AFB OH 45433

J. Eng. Mater. Technol 114(4), 409-415 (Oct 01, 1992) (7 pages) doi:10.1115/1.2904193 History: Received August 13, 1991; Revised March 17, 1992; Online April 29, 2008


A study was conducted to investigate the fatigue behavior of a cross-ply, [0/90]2s , laminate of silicon fiber reinforced titanium matrix composite, SCS-6/Ti-15-3 at an elevated temperature of 427°C. Two sets of tests, at frequencies 0.02 and 2 Hz, were run at different stress levels. Fatigue damage initiation and growth patterns were dependent on the specific test conditions of frequency and stress level. Microscopic analysis of the fatigued specimens revealed matrix failure mechanisms ranging from ductile failure to cleavage fracture. The results of this study showed that temperature and frequency, as well as stress levels, are important design considerations for this composite in fatigue loading applications.

Copyright © 1992 by The American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In