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Low Cycle Fatigue of Composite Laminates: A Damage-mode-sensitive Model

U.S. Army Research Laboratory, Aberdeen Proving Ground, Aberdeen, MD 21005, and ARL Group Center for Composite Materials, University of Delaware, Newark, DE 19716, USA; ICASE, MS 132C, NASA Langley Research Center, Hampton, VA 23681-2199v.m.harik{at}larc.nasa.gov;harik@icase.edu

T. A. Bogetti

U.S. Army Research Laboratory, Aberdeen Proving Ground, Aberdeen, MD 21005, and ARL Group Center for Composite Materials, University of Delaware, Newark, DE 19716, USA

Low cycle fatigue (LCF) behavior of composite laminates is investigated along with the associated micromechanical damage. At the ply level, fatigue damage is described by a damage-mode-sensitive model, which is based on a family of S–N curves that are tailored for various types of damage. Since the LCF conditions may involve high loads reaching up to 90% of the material ultimate-strength, the S–N curves reflect unique LCFfeatures such as non-cyclic and bi-linear corrections due to high property-degradation rates. The LCFcharacterization of laminates is based on authors’ previous research and other relevant studies. The proposed fatigue model is implemented in a laminate and finite element analysis, and a case of a notched laminated plate is analyzed to examine accumulation of fatigue damage at the ply level in the plate. The effective fatigue-damage is predicted by the new fatigue model and compared with experimental results.

Key Words: low cycle fatigue • composite laminates • S–N curves • notched plates • bending

Journal of Composite Materials, Vol. 37, No. 7, 597-610 (2003)
DOI: 10.1177/002199803029731


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