Analysis of fatigue and crack growth in carbon-fiber epoxy matrix composite laminates
Abstract
A study of high frequency fatigue in carbon-fiber reinforced composites has been undertaken. A comparison has been made between the fatigue behavior of crossply (0 / 90) and angleply (± 45) carbon/epoxy unnotched and notched laminates. Additionally, a micromechanical analysis of fracture surfaces performed by scanning electron microscopy was carried out to evaluate the micromechanisms that occurred during fatigue. Experimental observations indicate that fatigue damage consists of a combination of matrix cracks, longitudinal splitting, fiber fracture, delamination. In order to minimize the effects of residual strain due to temperature rise, a method is proposed for determining real fatigue strength at the level of variable load not lower than the fatigue limit, at which residual strains are minimal.
Keywords:
composite laminates / crack growth / fatigue / S - N curveSource:
Strength of Materials, 2003, 35, 5, 500-507
DOI: 10.1023/B:STOM.0000004538.77270.1e
ISSN: 0039-2316
PubMed:
Scopus: 2-s2.0-77953857237
Institution/Community
Tehnološko-metalurški fakultetTY - JOUR AU - Putić, Slaviša AU - Uskoković, Petar AU - Aleksić, Radoslav PY - 2003 UR - http://TechnoRep.tmf.bg.ac.rs/handle/123456789/499 AB - A study of high frequency fatigue in carbon-fiber reinforced composites has been undertaken. A comparison has been made between the fatigue behavior of crossply (0 / 90) and angleply (± 45) carbon/epoxy unnotched and notched laminates. Additionally, a micromechanical analysis of fracture surfaces performed by scanning electron microscopy was carried out to evaluate the micromechanisms that occurred during fatigue. Experimental observations indicate that fatigue damage consists of a combination of matrix cracks, longitudinal splitting, fiber fracture, delamination. In order to minimize the effects of residual strain due to temperature rise, a method is proposed for determining real fatigue strength at the level of variable load not lower than the fatigue limit, at which residual strains are minimal. T2 - Strength of Materials T1 - Analysis of fatigue and crack growth in carbon-fiber epoxy matrix composite laminates EP - 507 IS - 5 SP - 500 VL - 35 DO - 10.1023/B:STOM.0000004538.77270.1e ER -
@article{ author = "Putić, Slaviša and Uskoković, Petar and Aleksić, Radoslav", year = "2003", abstract = "A study of high frequency fatigue in carbon-fiber reinforced composites has been undertaken. A comparison has been made between the fatigue behavior of crossply (0 / 90) and angleply (± 45) carbon/epoxy unnotched and notched laminates. Additionally, a micromechanical analysis of fracture surfaces performed by scanning electron microscopy was carried out to evaluate the micromechanisms that occurred during fatigue. Experimental observations indicate that fatigue damage consists of a combination of matrix cracks, longitudinal splitting, fiber fracture, delamination. In order to minimize the effects of residual strain due to temperature rise, a method is proposed for determining real fatigue strength at the level of variable load not lower than the fatigue limit, at which residual strains are minimal.", journal = "Strength of Materials", title = "Analysis of fatigue and crack growth in carbon-fiber epoxy matrix composite laminates", pages = "507-500", number = "5", volume = "35", doi = "10.1023/B:STOM.0000004538.77270.1e" }
Putić, S., Uskoković, P.,& Aleksić, R.. (2003). Analysis of fatigue and crack growth in carbon-fiber epoxy matrix composite laminates. in Strength of Materials, 35(5), 500-507. https://doi.org/10.1023/B:STOM.0000004538.77270.1e
Putić S, Uskoković P, Aleksić R. Analysis of fatigue and crack growth in carbon-fiber epoxy matrix composite laminates. in Strength of Materials. 2003;35(5):500-507. doi:10.1023/B:STOM.0000004538.77270.1e .
Putić, Slaviša, Uskoković, Petar, Aleksić, Radoslav, "Analysis of fatigue and crack growth in carbon-fiber epoxy matrix composite laminates" in Strength of Materials, 35, no. 5 (2003):500-507, https://doi.org/10.1023/B:STOM.0000004538.77270.1e . .