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  • 1.
    Bru, Thomas
    et al.
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP. Chalmers University of Technology, Sweden.
    Olsson, Robin
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Gutkin, Renaud
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Vyas, Gaurav M.
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Use of the Iosipescu test for the identification of shear damage evolution laws of an orthotropic composite2017In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 174, p. 319-328Article in journal (Refereed)
    Abstract [en]

    The experimental evaluation of the shear response of fibre-reinforced plies is a requirement for accurate material models predicting progressive damage. In the first part of the paper, the quality of the Iosipescu shear test is investigated with full-field strain measurements and finite element analyses. In the second part, the in-plane and through-thickness shear response of an orthotropic carbon/epoxy uni-weave non-crimp fabric composite are compared, and the stress–strain curves used as input for two continuum damage mechanics models. Both models were able to predict accurately the nonlinear shear behaviour of the material. The model parameters and the damage evolution laws could easily be extracted from cyclic Iosipescu tests.

  • 2.
    Costa, Sergio
    et al.
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP. Chalmers University of Technology, Sweden.
    Gutkin, Renaud
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Olsson, Robin
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Mesh objective implementation of a fibre kinking model for damage growth with friction2017In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 168, p. 384-391Article in journal (Refereed)
    Abstract [en]

    A newly developed physically based model for the longitudinal response of laminated fibre-reinforced composites during compressive damage growth is implemented in a Finite Element (FE) software. It is a mesoscale model able to capture the physics of kink-band formation by shear instability, the influence of the matrix in supporting the fibres and the rotation of the fibres during compression, resulting in more abrupt failure for smaller misalignments. The fibre kinking response is obtained by solving simultaneously for stress equilibrium and strain compatibility in an FE framework. Strain softening creates pathological sensitivity when the mesh is refined. To make the model mesh objective, a methodology based on scaling the strain with the kink-band width is developed. The FE implementation of the current model is detailed with focus on mesh objectivity, and generalized to irregular meshes. The results show that the current model can be used to predict the whole kinking response in a 3D framework and thus account for the correct energy dissipation.

  • 3.
    Craven, R.
    et al.
    Imperial College London.
    Iannucci, L.
    Imperial College London.
    Olsson, Robin
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Homogenised non-linear soft inclusion for simulation of impact damage in composite structures2011In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 93, no 2, p. 952-960Article in journal (Refereed)
    Abstract [en]

    This paper presents the development of a homogenised non-linear soft inclusion which captures the geometric and material non-linearity of impact damage zone loaded in tension and compression. The homogenised non-linear soft inclusion can present a conservative worst case damage zone or use experimental data to mimic the behaviour of a particular damage zone in a simple and computationally efficient way that can be used as a structural design tool for composite structures subjected to impact. The development of the non-linear soft inclusion, implemented in an ABAQUS/Explicit VUMAT, is presented at element and coupon level. The non-linear soft inclusion is validated against experimental coupon data and produces a conservative worst case estimate in all cases investigated. © 2010 Elsevier Ltd.

  • 4.
    Grauers, Lisa
    et al.
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Olsson, Robin
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Gutkin, Renaud
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Energy absorption and damage mechanisms in progressive crushing of corrugated NCF laminates: Fractographic analysis2014In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 110, no 1, p. 110-117Article in journal (Refereed)
    Abstract [en]

    To develop reliable and physically based models for the crash behaviour of composite laminates, a thorough understanding of the failure mechanisms is crucial. Compression tests of corrugated Non-Crimp Fabric (NCF) laminates, made of carbon fibre unidirectional (UD) fabric with a [0/90]3S stacking sequence and epoxy, have been performed to study the energy absorbing damage mechanisms. Samples from the specimens have been studied with optical microscopy and Scanning Electron Microscopy (SEM) to identify the mechanisms involved in the crushing process. The specimens tested fail partly in bending and partly in pure compression with a mode I delamination separating these two regions. In the region failing in pure compression, the main damage mechanisms are kink band formation and matrix cracking of transverse bundles, whereas in the part failing in bending mixed mode delaminations, intralaminar shear fracture of axial bundles and kink band formation through parts of bundles are identified. © 2013 Elsevier Ltd.

  • 5.
    Hagnell, M. K.
    et al.
    KTH Royal Institute of Technology, Sweden.
    Langbeck, Björn
    RISE, Swerea, IVF.
    Åkermo, M.
    KTH Royal Institute of Technology, Sweden.
    Cost efficiency, integration and assembly of a generic composite aeronautical wing box2016In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 152, p. 1014-1023Article in journal (Refereed)
    Abstract [en]

    This paper presents a cost-efficiency study of part integration with respect to reduced assembly effort within aeronautical composite structures. The study is performed through the use, and continuous improvement upon, a previously developed cost model. Focus are on the assembly and basic inspection a wing box, part of a section of a full wing, where involved parts are all considered to be manufactured from carbon fibre reinforced plastic (CFRP). Treated cases range from traditional, mechanical joining, to high integration either through co-curing or co-bonding of composite structures. The outcome of presented cost study shows that increased integration decreases the overall production cost of said considered wing box. In general it is shown that co-curing or co-bonding reduces a number of cost-expensive assembly steps in comparison to mechanical joining

  • 6.
    Oddy, Carolyn
    et al.
    Chalmers University of Technology, Sweden.
    Ekermann, Tomas
    KTH Royal Institute of Technology, Sweden.
    Ekh, Magnus
    Chalmers University of Technology, Sweden.
    Fagerström, Martin
    Chalmers University of Technology, Sweden.
    Hallström, Stefan
    KTH Royal Institute of Technology, Sweden.
    Stig, Fredrik
    RISE - Research Institutes of Sweden, Materials and Production, IVF.
    Predicting damage initiation in 3D fibre-reinforced composites – The case for strain-based criteria2019In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 230, article id 111336Article in journal (Refereed)
    Abstract [en]

    Three dimensional (3D) fibre-reinforced composites have shown weight efficient strength and stiffness characteristics as well as promising energy absorption capabilities. In the considered class of 3D-reinforcement, vertical and horizontal weft yarns interlace warp yarns. The through-thickness reinforcements suppress delamination and allow for stable and progressive damage growth in a quasi-ductile manner. With the ultimate goal of developing a homogenised computational model to predict how the material will deform and eventually fail under loading, this work proposes candidates for failure initiation criteria. It is shown that the extension of the LaRC05 stress-based failure criteria for unidirectional laminated composites, to this class of 3D-reinforced composite presents a number of challenges and leads to erroneous predictions. Analysing a mesoscale representative volume element does however indicate, that loading the 3D fibre-reinforced composite produces relatively uniform strain fields. The average strain fields of each material constituent are well predicted by an equivalent homogeneous material response. Strain based criteria inspired by LaRC05 are therefore proposed. The criteria are evaluated numerically for tensile, compressive and shear tests. Results show that their predictions for the simulated load cases are qualitatively more reasonable. 

  • 7.
    Olsson, Robin
    et al.
    RISE, Swerea, SICOMP.
    Block, T. B.
    Faserinstitut Bremen e.V., Germany; Nordex Energy GmbH, Germany.
    Criteria for skin rupture and core shear cracking induced by impact on sandwich panels2015In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 125, p. 81-87Article in journal (Refereed)
    Abstract [en]

    Core shear cracking induced by impact on sandwich panels is a critical failure mode causing severe loss of structural performance. This paper reviews previous experimental and theoretical work in the area and derives improved closed form expressions for initiation of skin rupture and core shear cracking during impact on sandwich panels with foam cores. The criterion for skin rupture is also applicable to laminates without a core. It is shown that the skin rupture load limits the achievable core shear load, and that core shear cracking can be prevented by selecting a core thickness above a certain threshold value. The criteria are successfully validated by comparison with experimental results for a range of thicknesses of skins and cores in panels with carbon/epoxy skins and a Rohacell foam core. The criterion for skin rupture is also validated for plain laminates.

  • 8.
    Wilhelmsson, D.
    et al.
    GKN Aerospace Sweden AB, Sweden.
    Rikemanson, D.
    GKN Aerospace Sweden AB, Sweden.
    Bru, Thomas
    RISE - Research Institutes of Sweden, Materials and Production, SICOMP.
    Asp, L. E.
    Chalmers University of Technology, Sweden.
    Compressive strength assessment of a CFRP aero-engine component – An approach based on measured fibre misalignment angles2019In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 233, article id 111632Article in journal (Refereed)
    Abstract [en]

    In this paper we apply a recently developed methodology to assess the compressive strength of an aero-engine component based on measured fibre misalignment angles. The component is a fan outlet guide vane made from a carbon fibre reinforced polymer, which was manufactured and tested by GKN Aerospace in Sweden. The main novelty with this work is that kink-band formation is predicted from measurements of fibre misalignment angles with high spatial resolution in a real component. In addition, we validate the recently published “defect severity model” on unidirectional specimens of the same material system as the aerospace component. We confirm high accuracy of the model for prediction of compressive strength on unidirectional composite laminates. Further work is however needed to extend the methodology for cases where progressive damage leads to final failure. 

  • 9.
    Williams Portal, Natalie
    et al.
    RISE - Research Institutes of Sweden, Built Environment, CBI Swedish Cement and Concrete Research Institute.
    Flansbjer, Mathias
    RISE - Research Institutes of Sweden, Safety and Transport, Safety.
    Zandi, Kamyab
    RISE - Research Institutes of Sweden, Built Environment, CBI Swedish Cement and Concrete Research Institute.
    Wlasak, Lech
    Mostostal Warszawa SA, Poland.
    Malaga, Katarina
    RISE - Research Institutes of Sweden, Built Environment, CBI Swedish Cement and Concrete Research Institute.
    Bending behaviour of novel Textile Reinforced Concrete-foamed concrete (TRC-FC) sandwich elements2017In: Composite structures, ISSN 0263-8223, E-ISSN 1879-1085, Vol. 177, p. 104-118Article in journal (Refereed)
    Abstract [en]

    A novel sandwich element design consisting of two facings made of carbon reinforced Textile Reinforced Concrete (TRC), a low density foamed concrete (FC) core and glass fibre reinforced polymer (GFRP) connecting devices was experimentally investigated according to quasi-static and cyclic quasi-static fourpoint bending. Optical measurements based on Digital Image Correlation (DIC) were taken during testing to enable a detailed analysis of the bending behaviour and level of composite action. A model, verified by the experiments, was developed based on non-linear finite element analysis (NLFEA) to gain further insight on the failure mechanisms. Under both loading conditions, the bending behaviour of the TRCFC composite elements was characterized by favourable load bearing capacity, partial composite action, superior ductility and multiple fine cracking. The connecting devices were found to be the critical elements causing the initial failure mechanism in the form of localized pull-out within an element.

1 - 9 of 9
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  • ieee
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  • nn-NO
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