Finite element analysis of the behavior of bonded composite patches repair in aircraft structures

Islam El-Sagheer; Mai Taimour; Mariam Mobtasem; Amr Abd-Elhady; Hossam El-Din M. Sallam

doi:10.3221/IGF-ESIS.54.09

Finite element analysis of the behavior of bonded composite patches repair in aircraft structures

Authors

Islam El-Sagheer Department of Mechanical Design, Faculty of Engineering, University of Helwan, Egypt
Mai Taimour Department of Mechanical Design, Faculty of Engineering, University of Helwan, Egypt
Mariam Mobtasem Department of Mechanical Design, Faculty of Engineering, University of Helwan, Egypt
Amr Abd-Elhady Department of Mechanical Design, Faculty of Engineering, University of Helwan, Egypt
Hossam El-Din M. Sallam Materials Engineering Department, University of Zagazig, Zagazig, Egypt

DOI:

https://doi.org/10.3221/IGF-ESIS.54.09

Keywords:

Mode of mixity, J-integral, Aluminum alloy, 3-D FEM, Composite repair patch

Abstract

This paper aims to analyze the multi-effects of the glass fiber reinforced polymer (GFRP) composite patch to repair the inclined cracked 2420-T3 aluminum plate. Three-dimensional finite element method (FEM) was used to study the effect of GFRP composite patch with different stacking composite laminate sequence, [0°]₄, [90^o]₄, [45^o]₄, [0^o/45^o]_2s and [0°/90°]_4s on the crack driving force, J-integral, of inclined cracked 2420-T3 aluminum plate. Furthermore, the effects of patch geometry, number of layers, single or double side patch and crack incline angle are described.

The present results show that the patch has a high effect in case of a crack in pure mode I. Furthermore, the effectiveness of the composite patch is increasing with the crack length increases. Moreover, the efficiency of the composite patch has a high effect by changing the fiber orientation, the number of layers, and the single or double side patch.

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Published

23-09-2020

Issue

Vol. 14 No. 54 (2020): October 2020

Section

Fracture

License

This work is licensed under a Creative Commons Attribution 4.0 International License.

Copyright
Authors are allowed to retain both the copyright and the publishing rights of their articles without restrictions.

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How to Cite

Finite element analysis of the behavior of bonded composite patches repair in aircraft structures . (2020). Frattura Ed Integrità Strutturale, 14(54), 128-138. https://doi.org/10.3221/IGF-ESIS.54.09