Blast Resistance and Damage Modelling of Fibre Metal Laminates to Blast Loads
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Blast Resistance and Damage Modelling of Fibre Metal Laminates to Blast Loads Galal F. A. Mohamed · Costas Soutis · Alma Hodzic
Received: 13 July 2011 / Accepted: 4 August 2011 / Published online: 1 September 2011 © Springer Science+Business Media B.V. 2011
Abstract A robust and efficient computational model has been developed which is capable of modelling the dynamic non-linear behaviour of GLARE panels subjected to blast loadings. Numerical model validation have been performed considering case studies of GLARE panels subjected to a blast-type pressure pulse for which experimental data on the back-face deflection and post-damage observations were available. Excellent agreement of mid-point deflections and evidence of severe yield line deformation were shown and discussed against the performed blast tests. A further parametric study identified GLARE as a potential blast attenuating structure, exhibiting superior blast potential against monolithic aluminium plates. It was concluded that further work needed to be carried out to take into account the influence of geometry (cylindrical structures), pre-pressurisation effects and boundary conditions Keywords Fibre metal laminates · Blast resistance · Damage · Finite element analysis
1 Introduction As conventional metallic materials and their derivatives are increasingly being replaced in primary aerospace structures by fibre reinforced polymers, which offer lightweight and high specific properties; they continue to have a fundamental role in applications where composites have yet to be fully exploited [1]. Fibre metal laminates (FMLs) are a hybrid composite system developed as a lightweight alternative
G. F. A. Mohamed (B) · C. Soutis · A. Hodzic Department of Mechanical Engineering, University of Sheffield, Sheffield S1 3JD, UK e-mail: [email protected]
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Appl Compos Mater (2012) 19:619–636
(a)
(b)
Fig. 1 Configuration of GLARE laminates: a 3-2/1 and b 5-3/2
to aluminium which, amongst other attributes; offers superior fatigue resistance and ease of manufacture and repair [2]. GLARE (GLAss fibre REinforced laminate) is a class of FML for advanced aerospace structural applications. It consists of thin aluminium 2024-T3 sheets bonded together with unidirectional or biaxially reinforced adhesive pre-preg of high strength glass fibres (S2-glass/FM94). It is currently used in the manufacture of the upper fuselage skin and leading edges of the Airbus A380. The fuselage is a primary aerospace structure which is susceptible to damage in the form of fatigue cracks (due to widespread multi-site damage), environmental corrosion and impact/high strain rate damage. The damage in the form of the latter may arise from a bird strike or an on-board explosion. Although various types of GLARE configurations exists, depending on the structural requirement of the component, it is the cross-plied GLARE 3 and GLARE 5 with bi-directional reinforcements [2] which are of interest in impact applications, see Fig. 1 and Table 1 for details. It has been shown that, under low vel
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