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Geometrical parameters optimizations of scarf and double scarf bounded joint
Fekih, Sidi Mohamed,Madani, Kuider,Benbarek, Smail,Belhouari, Mohamed Techno-Press 2018 Advances in aircraft and spacecraft science Vol.5 No.3
The aim of this work is to optimize the geometrical parameters as the adhesive thickness and the beveled angle to reduce the edge effect of the scarf and V bounded joint. A finite element analysis is done to define the generated stresses in the bounded joint. The geometrical optimum is obtained using the Experimental Design Method. Results show that the double scarf (V) joint is better than the simple scarf bounded joint.
Optimization of scarf patch stacking sequences using the design of experiments method
Salma Aminallah,Sidi Mohamed Fekih,Abdelrahmen Sahli Techno-Press 2023 Advances in aircraft and spacecraft science Vol.10 No.4
In this study, The Von Mises stresses in composite plate loaded in tension and repaired by a boron/epoxy scarf patch were analyzed using the finite element method. The performance of the repairs depends on several parameters: the dimensions and the intrinsic properties of the patch and the adhesive which are dependent on each other. Therefore, the method of experiment designs is used to determine the interaction effect of different parameters (patch folds), their optimum and the most influential parameter. The optimum of stacking sequences allows reducing stresses significantly, and thus permits designers to improve the quality of repairs.
Numerical study of bonded composite patch repair in damaged laminate composites
Azzeddine, Nacira,Benkheira, Ameur,Fekih, Sidi Mohamed,Belhouari, Mohamed Techno-Press 2020 Advances in aircraft and spacecraft science Vol.7 No.2
The present study deals with the repair of composite structures by bonding composite patches. The composite structure is a carbon/epoxy laminate with stacking sequence [45/-45/0/90]S. The damaged zone is simulated by a central crack and repaired by bonding symmetrical composite patches. The repair is carried out using composite patches laminated from the same elemental folds as those of the cracked specimen. Three-dimensional finite element method is used to determine the energy release rate along the front of repaired crack. The effects of the repair technique used single or double patch, the stacking sequence of the cracked composite patch and the adhesive properties were highlighted on the variations of the fracture energy in mode I and mixed mode I + II loading.