Failure analysis of AA8011-pultruded GFRP adhesively bonded similar and dissimilar joints

In this work, a comparative failure analysis of aluminum (AA8011/AA8011) and glass fiber reinforced polyester (GFRP/GFRP) based similar and dissimilar joints is presented. The GFRP is prepared using pultrusion technique. Single lap joints are prepared by using Araldite R2011 epoxy as an adhesive. Th...

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Bibliographic Details
Published in:International journal of adhesion and adhesives 2019-04, Vol.90, p.97-105
Main Authors: Reddy, Nithin Simha, Jinaga, Ujwal Kishore, Charuku, Bharat Reddy, Penumakala, Pavan Kumar, Prasad, A.V.S. Siva
Format: Article
Language:English
Subjects:
Adherent plasticity
Adhesion tests
Adhesive joints
Adhesives
Aluminum base alloys
Bond strength
Bonded joints
Bonding strength
Cohesive Zone Model
Crack initiation
Crack propagation
Damage assessment
Failure analysis
Failure Mechanism
Failure mechanisms
Fiber reinforced materials
Finite element method
Glass fiber reinforced plastics
Glass fibers
Joints, Adhesive
Lap joints
Mathematical models
Peak load
Pultrusion
Shear strength
Stress analysis
Three dimensional analysis
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Summary:In this work, a comparative failure analysis of aluminum (AA8011/AA8011) and glass fiber reinforced polyester (GFRP/GFRP) based similar and dissimilar joints is presented. The GFRP is prepared using pultrusion technique. Single lap joints are prepared by using Araldite R2011 epoxy as an adhesive. The lap joints are then tested under tension to estimate the average shear strength of the assembly. It is observed that the average bond strength of AA8011/AA8011 is lesser than that of the GFRP/GFRP joint. The failure of similar joints occurred by fracture within the adhesive. The dissimilar joint is failed predominantly by interface debonding. Further, a detailed three dimensional stress analysis of the joints is carried out using finite element method (FEM). The damage analysis of adhesive layer is carried out by coupling FEM with cohesive zone model (CZM). The stress, damage distributions and failure mechanisms are compared for similar joints in detail. A failure mechanism is proposed for AA8011/AA8011 type joint that favours a rapid crack growth in the adhesive after crack initiation, which is responsible for lesser bond strength. The increase in overlap length has positive effect that the peak load increases proportionally with overlap length.
ISSN:0143-7496
1879-0127
DOI:10.1016/j.ijadhadh.2019.02.004