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RESEARCH PAPERS

Fatigue Crack Propagation in 8- and 22-Layer 7075-T6 Aluminum Alloy Laminates

[+] Author and Article Information
N. J. Pfeiffer, J. A. Alic

Department of Mechanical Engineering, Wichita State University, Wichita, Kan.

J. Eng. Mater. Technol 100(1), 32-38 (Jan 01, 1978) (7 pages) doi:10.1115/1.3443447 History: Received April 05, 1977; Revised July 22, 1977; Online August 17, 2010

Abstract

Rates of fatigue crack propagation have been determined for adhesively bonded 7075-T6 laminates having a crack divider geometry. Two lamina thicknesses were used, the resulting laminates having either 8 or 22 layers. Crack growth rates were generally within the same range as for monolithic 7076-T6 alloy, and were somewhat slower in the 22-layer laminates than in those with 8 layers. Instances of decreasing crack propagation rate with increasing stress intensity amplitude, as well as of crack arrest, were observed. These are interpreted in terms of interactions between the layers during the progressive transition from a flat mode of crack growth to a slant mode.

Copyright © 1978 by ASME
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