A Three-Dimensional Ply Failure Model for Composite Structures

International Journal of Aerospace Engineering (Impact Factor: 0.48). 01/2009; DOI: 10.1155/2009/486063
Source: DOAJ

ABSTRACT A fully 3D failure model to predict damage in composite structures subjected to multiaxial loading is presented in this paper. The formulation incorporates shear nonlinearities effects, irreversible strains, damage and strain rate effects by using a viscoplastic damageable constitutive law. The proposed formulation enables the prediction of failure initiation and failure propagation by combining stress-based, damage mechanics and fracture mechanics approaches within an unified energy based context. An objectivity algorithm has been embedded into the formulation to avoid problems associated with strain localization and mesh dependence. The proposed model has been implemented into ABAQUS/Explicit FE code within brick elements as a userdefined material model. Numerical predictions for standard uniaxial tests at element and coupon levels are
presented and discussed.

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Available from: Sergio Almeida, Sep 28, 2015
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    • "Experiments were developed separately to determine ply fracture energies, for which no standard tests currently exist [23] [26]. An explicit damage model for high velocity applications was developed by Raimondo et al. [27] [28], while Donadon et al. [29] [30] formulated a nonlinear shear law including gradual stiffness reduction and used an objectivity algorithm to obtain characteristic lengths in non-structured meshes. The explicit damage model developed here incorporates physically-based failure criteria, a nonlinear shear law and a crack band model to mitigate mesh sensitivity. "
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    ABSTRACT: Three-dimensional explicit finite element modelling is used to predict the quasi-static bearing response of typical countersunk composite fuselage skin joints. In order to accurately simulate bearing failure, a user-defined 3D composite damage model was formulated for Abaqus/Explicit and included Puck failure criteria, a nonlinear shear law and a crack band model to mitigate mesh sensitivity. A novel approach was developed to employ characteristic element lengths which account for the orientation of composite ply cracks in the Abaqus/Explicit solver. Resulting models accurately predicted initial joint sticking behaviour and the elastic loading response of single-bolt and three-bolt joints, but preliminary predictions of bearing failure onset were overly-conservative. Improved failure predictions were obtained by utilising a fracture energy for compressive fibre failure which was considered more relevant for simulating bearing damage. The explicit models were exceptionally robust, showing capability to predict extensive hole crushing. Methods of dramatically improving joint model efficiency were highlighted.
    Composite Structures 02/2014; 108(1):963-977. DOI:10.1016/j.compstruct.2013.10.033 · 3.32 Impact Factor
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    • "The ballistic impact simulations were carried out using three different material models: (i) Johnson-Cook model [1] to predict the material behavior of the projectile; (ii) JH-2 model [2] to predict the material behavior of the ceramic. This model is suitable to predict the behavior of brittle materials subjected to extreme loading; (iii) a 3-D progressive failure model [3] to predict the structural response of the composite base. The formulation of this model is based on the Continuum Damage Mechanics (CDM) approach and enables the control of the energy dissipation associated with each failure mode regardless of mesh refinement and fracture plane orientation by using a smeared cracking formulation; (iv) a contact-logic to predict debonding between the ceramic plate and the composite base [4]. "
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    ABSTRACT: This paper presents a ballistic impact simulation of an armour-piercing projectile in hybrid ceramic/fiber reinforced composite armour. The armour is composed by an alumina plate and an ultra high molecular weight polyethylene composite. In order to model the armour behavior three different constitutive models were formulated and implemented into ABAQUS/Explicit finite element code. Comparisons between numerical predictions and experimental results in terms of damage shape/extent and V-50 are also presented and discussed in the paper.
    International Journal of Impact Engineering 05/2012; 43. DOI:10.1016/j.ijimpeng.2011.12.001 · 2.20 Impact Factor
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    ABSTRACT: This paper presents a numerical study on the impact resistance of composite shells laminates using an energy based failure model. The damage model formulation is based on a methodology that combines stress based, continuum damage mechanics (CDM) and fracture mechanics approaches within a unified procedure by using a smeared cracking formulation. The damage model has been implemented as a user-defined material model in ABAQUS FE code within shell elements. Experimental results obtained from previous works were used to validate the damage model. Finite element models were developed in order to investigate the pressure and curvature effects on the impact response of laminated composite shells.
    Composite Structures 12/2010; 93(1):142-152. DOI:10.1016/j.compstruct.2010.06.006 · 3.32 Impact Factor
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