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

Autor
Pitta, S.; de la Mora, V.; Roure, F.; Crespo, D.; Rojas, J.I.
Tipus d'activitat
Article en revista
Revista
Composite structures
Data de publicació
2018-10-01
Volum
201
Pàgina inicial
276
Pàgina final
290
DOI
https://doi.org/10.1016/j.compstruct.2018.06.002 Obrir en finestra nova
Projecte finançador
Transicions de fase, polimorfisme, vidres i dinàmica de la metastabilitat
Vidrios orgánicos y metálicos: dinámica, recristalización y propiedades vibracionales
Repositori
http://hdl.handle.net/2117/118582 Obrir en finestra nova
URL
https://www.sciencedirect.com/science/article/pii/S0263822317339284 Obrir en finestra nova
Resum
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 ...
Citació
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.
Paraules clau
Adhesive, Aircraft lap joint, Aluminium alloy, Carbon fibre reinforced epoxy, Finite element analysis, Rivet
Grup de recerca
GCM - Grup de Caracterització de Materials
REMM - Recerca en Estructures i Mecànica de Materials

Participants