Advances in aircraft and spacecraft science

  • 제4권6호
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  • Pages.679-699
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  • 2017
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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DOI QR코드

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Impact of composite patch on the J-integral in adhesive layer for repaired aluminum plate

  • Kaci, D. Ait (Laboratoire Mecanique Physique des Materiaux (LMPM), Department of Mechanical Engineering, University of SidiBel Abbes) ;
  • Madani, K. (Laboratoire Mecanique Physique des Materiaux (LMPM), Department of Mechanical Engineering, University of SidiBel Abbes) ;
  • Mokhtari, M. (Laboratoire Mecanique Physique des Materiaux (LMPM), Department of Mechanical Engineering, University of SidiBel Abbes) ;
  • Feaugas, X. (LaSIE, UMR7356, Laboratoire des Sciences de l'Ingenieur pour l'Environnement, Universite La Rochelle) ;
  • Touzain, S. (LaSIE, UMR7356, Laboratoire des Sciences de l'Ingenieur pour l'Environnement, Universite La Rochelle)
  • 투고 : 2017.05.26
  • 심사 : 2017.07.31
  • 발행 : 2017.11.25
⟨ 이전 논문 다음 논문 ⟩

초록

The aim of this study is to perform a finite element analysis of the Von Mises stresses distribution in the adhesive layer and of the J-Integral for a damaged plate repaired by a composite patch. Firstly, we study the effect of the fiber orientation, especially the position of the layers that have orientation angle different of $0^{\circ}$ from the first layer which is in all cases of our study oriented at ($0^{\circ}$) on the J-Integral. Secondly, we evaluate the effects of the mechanical properties of the patch and the use of a hybrid patch on the reduction of stresses distribution and J-Integral. The results show clearly that the stacking sequence for the composite patch must be selected to absorb optimally the stresses from the damaged area and to position the various layers of the composite under the first layer whose fibers orientation will remain in all cases equal to $0^{\circ}$. The use of a hybrid composite reduces significantly the J-Integral and the stresses in both damaged plate and the adhesive layer.

키워드

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