Effect of Disbonds on the Fatigue Endurance of Composite Scarf Joints

Abstract:

The certification of scarf repairs requires that the repair is capable of handling flight loads in the presence of disbonds. This paper presents a study of the fatigue disbond growth behaviour of scarf joints. By determining the strain energy release rates of a disbond in a scarf joint subjected to a unit load, a predictive model based on linear elastic fracture mechanics is presented, which is shown to correlate well with experimental results. This method offers a promising technique of predicting the fatigue life of composite scarf joints with disbonds.

• Periodical: Advanced Materials Research (Volumes 891-892)
• Pages: 191-196
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.891-892.191
• Online since: March 2014
• Authors: J.Y. Goh, S. Georgiadis, Adrian C. Orifici, Chun H. Wang*
• Keywords: Composite, Damage Tolerance, Finite Element, Fracture Mechanics, Scarf Joint

References

[1] FAA, Composite Aircraft Structure: Advisory Circular (AC) 20-107B, (2010).

[2] Wang, C.H., Gunnion, A.J., Orifici, A.C., and Rider, A., Residual strength of composite laminates containing scarfed and straight-sided holes. Composites Part A, 2011. 42: p.1951-(1961).

DOI: 10.1016/j.compositesa.2011.08.020

[3] Goh, J.Y., Georgiadis, S., Orifici, A.C., and Wang, C.H., Effects of bondline flaws on the damage tolerance of composite scarf joints. Composites Part A: Applied Science and Manufacturing, 2013. 55: pp.110-119.

DOI: 10.1016/j.compositesa.2013.07.017

[4] Kim, M.K., Elder, D.J., Wang, C.H., and Feih, S., Interaction of laminate damage and adhesive disbonding in composite scarf joints subjected to combined in-plane loading and impact. Composite Structures, 2012. 94(3): pp.945-953.

DOI: 10.1016/j.compstruct.2011.10.017

[5] Goh, J., Georgiadis, S., Orifici, A., and Wang, C., Effects of bondline flaws on the damage tolerance of composite scarf joints. Composites Part A: Applied Science and Manufacturing, (2013).

DOI: 10.1016/j.compositesa.2013.07.017

[6] Benzeggagh, M.L. and Kenane, M., Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus. Composites Science and Technology, 1996. 56(4): pp.439-449.

DOI: 10.1016/0266-3538(96)00005-x

[7] Camanho, P.P., Davila, C.G., and de Moura, M.F., Numerical Simulation of Mixed-Mode Progressive Delamination in Composite Materials. Journal of Composite Materials, 2003. 37(16): pp.1415-1438.

DOI: 10.1177/0021998303034505

[8] ACG, ACG VTM260 Series. Variable temperature moulding prepreg system, 2009, Advanced Composites Group Ltd: Derbyshire, UK.

[9] Pingkarawat, K., Wang, C.H., Varley, R.J., and Mouritz, A.P., Healing of fatigue delamination cracks in carbon–epoxy composite using mendable polymer stitching. Journal of Intelligent Material Systems and Structures, 2013: p. 1045389X13505005.

DOI: 10.1177/1045389x13505005

[10] Abaqus Version 6. 10 Documentation2009, Rhode Island, USA: Abaqus Inc.

[11] Wang, C.H. and Gunnion, A.J., On the design methodology of scarf repairs to composite laminates. Composites Science and Technology, 2008. 68(1): pp.35-46.

DOI: 10.1016/j.compscitech.2007.05.045