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

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Published Sep 23, 2020
DOI https://doi.org/10.3221/IGF-ESIS.54.09

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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

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, [90o]4, [45o]4, [0o/45o]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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    Issue
    Vol. 14 No. 54 (2020): October 2020
    Section
    Fracture

    How to Cite

    El-Sagheer, I. (2020) “Finite element analysis of the behavior of bonded composite patches repair in aircraft structures ”, Frattura ed Integrità Strutturale, 14(54), pp. 128–138. doi: 10.3221/IGF-ESIS.54.09.
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