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On the static strength of aluminium and carbon fibre aircraft lap joint repairs

Author
Pitta, S.; de la Mora, V.; Roure, F.; Crespo, D.; Rojas, J.I.
Type of activity
Journal article
Journal
Composite structures
Date of publication
2018-10-01
Volume
201
First page
276
Last page
290
DOI
https://doi.org/10.1016/j.compstruct.2018.06.002 Open in new window
Project funding
Organic and Metallic Glasses: Dynamics, Recrystallization and Vibrational Properties
Transicions de fase, polimorfisme, vidres i dinàmica de la metastabilitat
Repository
http://hdl.handle.net/2117/118582 Open in new window
URL
https://www.sciencedirect.com/science/article/pii/S0263822317339284 Open in new window
Abstract
The behaviour of various aircraft lap joint repair configurations is investigated experimentally and numerically under static loading. The lap joints consist of aluminium alloy (AA) 2024-T3 substrates repaired with twin single-sided AA 2024-T3 or Carbon Fibre Reinforced Epoxy (CFRE) doublers. Pure riveted, pure bonded and hybrid (riveted and bonded) joints of metal–metal and metal–composite configurations are investigated. From experimental results, joints with adhesive bond showed nearly 5 ...
Citation
Pitta, S., de la Mora, V., Roure, F., Crespo, D., Rojas, J.I. On the static strength of aluminium and carbon fibre aircraft lap joint repairs. "Composite structures", 1 Octubre 2018, vol. 201, p. 276-290.
Keywords
Adhesive, Aircraft lap joint, Aluminium alloy, Carbon fibre reinforced epoxy, Finite element analysis, Rivet
Group of research
GCM - Group of Characterization of Materials
REMM - Structures and Mechanics of Materials Research

Participants