Fatigue Behavior of a Cross-Ply Metal Matrix Composite at Elevated Temperature Under the Strain Controlled Mode

[+] Author and Article Information
B. P. Sanders, S. Mall, L. B. Dennis

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

J. Eng. Mater. Technol 119(4), 422-428 (Oct 01, 1997) (7 pages) doi:10.1115/1.2812279 History: Received February 24, 1996; Revised February 03, 1997; Online November 27, 2007


A study was conducted to investigate the fatigue behavior of a cross-ply metal matrix composite subjected to fully-reversed, strain-controlled fatigue cycling at elevated temperature. The stress-strain response, maximum and minimum stresses, and modulus during cycling were analyzed to characterize the macro-mechanical behavior. Additionally, microscopy and fractography were conducted to identify damage mechanisms. Damage always initiated in the 90 deg plies, but the governing factor in the fatigue life was damage in the 0 deg plies. The dominant failure mode was fracturing of fibers in the 0 deg plies when the maximum strain was greater than 0.55 percent, but the dominant failure mode was matrix cracking when the maximum strain was less than 0.55 percent. Combining the fatigue life data with the macro-mechanical and microscopic observations, a fatigue life diagram was developed and partitioned into three regions. These regions showed relationships between the maximum applied strain and the dominant damage mechanisms. Also, on a strain range basis, the fatigue lives of the specimens tested under the strain-controlled mode in this study were compared with its counterpart under the load-controlled mode of the previous study. It was found that the fatigue lives for these two conditions were the same within the experimental scatter.

Copyright © 1997 by The American Society of Mechanical Engineers
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