Parameter Study of Numerical Analysis on Low-Velocity Impact of GLARE 5 Fibre-Metal Laminates

Abstract:

The impact performance play an important role to marine material. A numerical methodology including user material subroutine VUMAT, Johnson–Cook flow stress model and surface-based cohesive behaviour is employed to simulate the damage of the impact of GLARE 5 fibre-metal laminates (FML). Not only histories of absorbed energy, deflection, contact force are presented in our simulation, but the interface delamination is also investigated. After parameter study, suitable fracture energy in surface-based cohesive behaviour was found.

• Periodical: Advanced Materials Research (Volumes 1033-1034)
• Pages: 515-518
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.1033-1034.515
• Online since: October 2014
• Authors: Yun Wan*, Xin Lei Huang, Li Min Zhou
• Keywords: GLARE 5, Low-Velocity Impact, Parameter Study, Simulation of Impacted Responses

References

[1] A. Vlot. Impact properties of fibre metal laminates. Compos. Eng. 3 (1993) 911–927.

[2] A. Vlot, J.W. Gunnink, editors. Fiber metal laminates e an introduction. Dor-drecht, The Netherlands: Kluwer Academic Publisher; (2001).

[3] S.H. Song, Y.S. Byun, T.W. Ku, W.J. Song, J. Kim, B. S Kang, Experimental and numerical investigation on impact performance of carbon reinforced aluminium laminates. J. Mater. Sci. Technol. 26 (2010) 327-332.

DOI: 10.1016/s1005-0302(10)60053-9

[4] H. Seo, J. Hundley, H.T. Hahn, J.M. Yang, Numerical simulation of glass-fiber-reinforced aluminium laminates with diverse impact damage. AIAA J. 48 (2010) 676-687.

DOI: 10.2514/1.45551

[5] M. Sadighi, T. Parnanen, R.C. Alderliesten, M Sayeaftabi, R Benedictus, Experimental and numerical investigation of metal type and thickness effects on the impact resistance of fiber-metal laminates. Appl. Composite Mater. 19 (2012) 545-559.

DOI: 10.1007/s10443-011-9235-6

[6] A. Seyed Yaghoubi, Y. Liu, B. Liaw. Low-velocity impact on Glare 5 fiber-metal laminates: influences of specimen thickness and impactor mass. J. Aerosp. Eng., 25 (2012) 409–420.

DOI: 10.1061/(asce)as.1943-5525.0000134

[7] G.R. Johnson, W.H. Cook. A constitutive model and data for metals subjected to large strains, high strain rates and high temperatures. In: Proceedings of the seventh international symposium on ballistics; 1983. The Hague, Netherland. p.541–547.

[8] G. Kay. Failure modeling of titanium–61–4V and 2024-T3 aluminum with the Johnson–Cook Material Model. In: US Department of Energy; (2002).

DOI: 10.2172/15006359

[9] D. Lesuer. Experimental investigations of material models for Ti–6AL4V and 2024-T3; 1999. U.S. Department of Energy.

[10] Z. Hashin. Failure criteria for unidirectional fiber composites. J. Appl. Mech. 47 (1980) 329–334.

[11] S.C. Tan. A progressive failure model for composite laminates containing opening. J. Compos. Mater. 25 (1991) 556-577.

[12] Abaqus 6. 9 Example Problems Manual 1. 4. 6. Providence, RI, USA: Dassault Systèmes Simulia Corporation; (2010).