Experimental and numerical investigation of fatigue crack growth in aluminum plates repaired by FML composite patch

M. Rahmani Kalestan (Faculty of Mechanical Engineering, S.R.T.T. University, Tehran, Iran)
H. Moayeri Kashani (Department of Mechanical Engineering, K.N. Toosi University of Technology, Tehran, Iran)
A. Pourkamali Anaraki (Faculty of Mechanical Engineering, S.R.T.T. University, Tehran, Iran)
F. Ashena Ghasemi (Faculty of Mechanical Engineering, S.R.T.T. University, Tehran, Iran)

International Journal of Structural Integrity

ISSN: 1757-9864

Publication date: 11 November 2014

Abstract

Purpose

The purpose of this paper is to use the fiber metal laminates (FML) composites as a patch for repairing a single notched specimen made of AL1035 aluminum alloy. The FML composite patch was bonded on one side of the cracked specimens by adhesive Araldite 2015. Then the fatigue crack growth tests were conducted on the specimens and the effects of both FML patch lay-up sequence and pre-crack angle on the fatigue life were investigated. Finally, the effect of repairing on the fracture parameters (SIF and crack propagation direction) at the crack front has also been calculated using three-dimensional finite element analysis.

Design/methodology/approach

The fatigue crack growth tests were conducted on the specimens and the effects of both FML patch lay-up sequence and pre-crack angle on the fatigue life were investigated.

Findings

The results show that the fatigue life of the patched specimens with inclined crack increased approximately 2-6.02 times compared to the un-patched specimens. In addition, the fatigue crack growth rate decreased significantly when the patch was used. Generally, the FML patch with Plate-Fiber-Fiber-AL lay-up has more efficiency than other lay-up sequences.

Originality/value

Recently, composite patches are used in the structure repair processes to increase the service life of cracked components. The bonded patch method is one of the efficient methods among repairing methods. Today, the FMLs are used in the aircraft structures as a replacement of high-strength aluminum alloys due to their lightweight and high-strength properties. Many researches have been performed on single and double side repaired panels using composite patches. In this study, the FML composites have been used as a patch for repairing a single notched specimen made of AL1035 aluminum alloy.

Keywords

Acknowledgements

This research is supported by the Shahid Rajaee Teacher Training University under contract number 29327/7.

Citation

Rahmani Kalestan, M., Moayeri Kashani, H., Pourkamali Anaraki, A. and Ashena Ghasemi, F. (2014), "Experimental and numerical investigation of fatigue crack growth in aluminum plates repaired by FML composite patch", International Journal of Structural Integrity, Vol. 5 No. 4, pp. 242-252. https://doi.org/10.1108/IJSI-08-2013-0019

Publisher

:

Emerald Group Publishing Limited

Copyright © 2014, Emerald Group Publishing Limited

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