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The
Laboratory, AeroDamageLab,
was
established
in
the
2009
at
Faculty of Mechanical Engineering and Naval
Architecture (FMENA), University of Zagreb, within the framework of the
Technology Project TP-07/0120-30
“Numerical
Modelling
of
Damage
in
Aeronautical
Structures”. One of
the objectives is to continue cooperation with flag carrier
airline „Croatia
Airlines“ in the development of technology aimed at
determining foreign object damage (e.g. due to bird impact) in the
composite,
sandwich as well as metallic aeronautical structures.
The
methodology is based on
explicit integration methods
used within finite element program Abaqus/Explicit, along with the
corresponding failure criteria at impact on aluminium, sandwich or
composite structures. Special attention was given to the modelling of
impactor/bird (using EOS, ALE) in order to be able to compare numerical
results with the available references.
The
focus of current research activities is application of multiscale methodlogy in the
damage modelling of fibre reinforced composite materials. The High Fidelity Generalized Method
of Cells (HFGMC) has been used as a micromechanical model to model damage processes at the constituent level.
Coupling between the micromechanical model and the finite element analysis has been achieved via Abaqus/Explicit
user material subroutine VUMAT.
Furthermore,
the Laboratory
is the focal point for
development of numerical methods in the mechanics of composites
engineering.
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D. Ivančević, I. Smojver,
Explicit Multiscale Modelling of Impact Damage on Laminated Composites – Part I: Validation of the Micromechanical Model,
Composite structures. 145 (2016); 248–258
doi: 10.1016/j.compstruct.2016.02.048
D. Ivančević, I. Smojver,
Explicit Multiscale Modelling of Impact Damage on Laminated Composites – Part II: Multiscale Analyses,
Composite structures. 145 (2016); 259–268
doi: 10.1016/j.compstruct.2016.02.049
D. Ivančević, I. Smojver,
Micromechanical Damage Modelling using a Two-scale Method for Laminated Composite Structures. Composite Structures. 108 (2014) ; 223–233
doi: 10.1016/j.compstruct.2013.09.028
I. Smojver, D. Ivančević,
Advanced Modelling of Bird Strike on High Lift Devices Using Hybrid
Eulerian-Lagrangian Formulation. Aerospace science and technology. 23 (2012) ; 224–232
doi: 10.1016/j.ast.2011.07.010
D. Ivančević, I. Smojver, Multiscale Approach to Damage Analysis of
Laminated Composite Structures, Simulia Community Conference, 15.05. –
17.05. 2012., Providence, RI
D. Ivančević, I. Smojver, Hybrid Approach in Bird Strike Damage Prediction on Aeronautical
Composite Structures, Composite Structures, 94, 15 – 23, 2011
doi: 10.1016/j.compstruct. 2011.07.028
I.
Smojver,
D. Ivančević, Bird Strike Damage Analysis
in Aircraft Structures Using Abaqus/Explicit and Coupled Eulerian Lagrangian Approach
, Composites Science and Technology, 71, 489 – 498, 2011
doi: 10.1016/j.compscitech.2010.12.0241
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Project
Laboratory for Numerical Modelling of Damage in Aeronautical Structures
- AeroDamageLab
University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture
Department of Aeronautical Engineering
I. Lučića 5, HR-10000 Zagreb, Croatia
Permanent members:
Prof. Dr. Sc. Ivica
Smojver
Asst. Prof.
Darko
Ivančević
phone &
fax: +385 1 6168 267 (Prof. Dr. Sc. Ivica Smojver)
e-mail: ismojver@fsb.hr
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Administrator LAST CHANGE: 28.03.2017 |
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NEWS
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LEAFLET
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INTRANET
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Micromechanical stress distribution within the unit cell [GPa]
- 100 x 100 subcells.
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Effect of unit cell refinement on distribution of Micromechanics of Failure matrix damage initiation criterion.
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Comparison of ply-level matrix failure criteria with micromechanical failure criteria.
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1.81 kg bird impact on inboard flap at
100 m/s, CEL model. Contours of Hashin’s fiber tensile failure
criterion are shown.
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Penetration of the lower flap skin
impacted by a 1.81 kg bird at 100 m/s. Eulerian Volume Fraction
contours are shown, cross-sectional view.
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Slat skin deflection impacted by a 1.81
kg bird at 100 m/s.
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CEL model of bird strike on the flap
structure.
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Comparison of Hashin's tensile failure
criteria of lower flap skin impacted by a 0.45 kg and a 1.81 kg bird.
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Deformation of the bird material during
the impact.
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Penetration of the 1.81 kg Lagrangian
bird model through the flap leading edge sandwich structure.
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