Failure Mechanisms of Composite Plates With a Circular Hole Under Remote Biaxial Planar Compressive Loads

[+] Author and Article Information
A. R. Khamseh

Chrysler Motors

A. M. Waas

Department of Aerospace Engineering, College of Engineering, University of Michigan, Ann Arbor, MI 48109-2118

J. Eng. Mater. Technol 119(1), 56-64 (Jan 01, 1997) (9 pages) doi:10.1115/1.2805974 History: Received August 19, 1995; Revised June 22, 1996; Online December 05, 2007


We report the results of an experimental investigation carried out for the analysis of failure mechanisms in fibrous laminated composite plates containing stress raisers, in the form of circular cutouts, under static biaxial planar compressive loading (i.e., compression in the two inplane orthogonal directions). A series of biaxial tests were carried out with 48 ply graphite/epoxy composites of varying fiber orientation. In all cases, the hole diameter to plate width aspect ratio remained in a range suitable for infinite plate assumptions. Fiber microbuckling, fiber kink banding, and fiber/matrix debonding are identified as the dominant failure mechanisms.

Copyright © 1997 by The American Society of Mechanical Engineers
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