Copy the page URI to the clipboard
Irving, P. E.; Zhang, X.; Doucet, J.; Figueroa-Gordon, D.; Boscolo, M.; Heinimann, M.; Shepherd, G.; Fitzpatrick, M. E. and Liljedahl, D.
(2011).
DOI: https://doi.org/10.1007/978-94-007-1664-3_59
Abstract
This paper explores the viability of the bonded crack retarder concept as a device for life extension of damage tolerant aircraft structures. Fatigue crack growth behaviour in metallic substrates with bonded straps has been determined. SENT and M(T) test coupons and large scale skin-stringer panels were tested at constant and variable amplitude loads. The strap materials were glass fibre polymer composites, GLARE, AA7085 and Ti-6Al- 4V. Comprehensive measurements were made of residual stress fields in coupons and panels.
A finite element model to predict retardation effects was developed. Compared to the test result, predicted crack growth life had an error range of -29% to 61%.
Mechanisms and failure modes in the bonded strap reinforced structures have been identified. The strap locally reduces substrate stresses and bridges the crack faces, inhibiting crack opening and reducing crack growth rates. In the absence of residual stress, global stiffness ratio accounts for effects of both strap modulus and strap cross section area. In elevated temperature cure adhesives, retardation performance was best in aluminium and GLARE strap materials, which have the closest thermal expansion coefficient to the substrate. Strap materials of high stiffness and dissimilar thermal expansion coefficient such as titanium had poor retardation characteristics.
CORE (COnnecting REpositories)
CORE (COnnecting REpositories)
