Numerical Simulations of Inter-laminar Damage Evolution in a Composite Wing Box
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Numerical Simulations of Inter-laminar Damage Evolution in a Composite Wing Box A. Riccio & A. Raimondo & R. Borrelli & U. Mercurio & D. Tescione & F. Scaramuzzino
Received: 25 July 2013 / Accepted: 13 September 2013 # Springer Science+Business Media Dordrecht 2013
Abstract In this paper, a numerical study has been carried out on skin delamination and skin-stringer debonding growth in a composite wing-box under compressive loading conditions. The adopted numerical models use the Virtual Crack Closure Technique to simulate the inter-laminar damage evolution and the numerical analyses have been performed by means of the FEM code ABAQUS and B2000++. The obtained numerical results have been assessed and compared each other in terms of delaminated area evolution, delamination growth initiation load and strain distributions. In order to investigate the effectiveness of the adopted numerical platforms in predicting the evolution of inter-laminar damages, comparisons with experimental data, in terms of load displacement curves and strains in the debonding area, have been also introduced. Keywords Skin delamination . Skin-stringer debonding . Damage growth . FEM
1 Introduction Due to their high specific strength and stiffness, Carbon Fibers Reinforced Plastics (CFRP) are commonly considered particularly suitable for aerospace structural applications. However, their failure mechanisms are complex and not completely predictable (especially the inter-laminar failure mechanism such as the delaminations) and this is the main reason why the CFRP integration into aerospace Industry has been generally slow in the last 20 years. Indeed the lack of robust numerical tools, able to take into account the damage tolerance of composite structures, has led to over-conservative designs, not fully realizing the promised economic benefits of Composites.
A. Riccio : A. Raimondo (*) : F. Scaramuzzino Department of Industrial and Information Engineering, Second University of Naples, via Roma n29, 81031 Aversa, Italy e-mail: [email protected] R. Borrelli : U. Mercurio : D. Tescione C.I.R.A. Italian Aerospace Research Center, via maiorise SN, 81043 Capua, Italy
Appl Compos Mater
In the present paper, this issue is addressed by suggesting an integrated approach for the inter-laminar damage management of aircraft composite structures monitored by embedded optic fibers. The mechanical behavior of composite structures with inter-laminar damages has been widely investigated in literature by experimental tests and by predictive numerical tools. Examples of experimental research activities aimed at increasing the knowledge on composites inter-laminar damages and to build experimental databases for the validation of brand new numerical tools are given in [1–5]. In particular, experiments on failure behavior of composite materials with enhanced toughness properties can be found in [6–8]. Furthermore, developments on simplified mono and two-dimensional predictive numerical models, accounting for the presence of trough-the-width delaminations
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