Citation:
P.E. Irving, X. Zhang, J. Doucet, D. Figueroa-Gordon, M. Boscolo, M. Heinimann, G. Shepherd, M.E. Fitzpatrick, D. Liljedahl. Life extension techniques for aircraft structures-Extending durability and
promoting damage tolerance through bonded crack retarders. ICAF 2011 Structural Integrity : Influence of Efficiency and Green Imperatives : Proceedings of the 26th Symposium of the International Committee on Aeronautical Fatigue. Canada, pp753-770. Ed. Jerzy Lomorowski
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.
