Numerical simulation of bird strike damage prediction in airplane flap structure

Smojver, Ivica; Ivančević, Darko

doi:10.1016/j.compstruct.2009.12.006

Cited by 68 publications

(40 citation statements)

References 9 publications

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“…The CEL bird strike damage prediction capability has been demonstrated through comparison with numerical results obtained by the Lagrange bird model used in the preceding work [8]. The point of impact and bird velocity vector have been chosen according to the landing flight parameters of a large transport aircraft.…”

Section: Discussionmentioning

confidence: 99%

“…To investigate the advantages of the Eulerian bird modelling approach the results of this analysis have also been compared with Lagrangian bird model results presented in [8]. The results of the analyses are shown in Fig.…”

Section: Validation Of Cel Bird Modelmentioning

confidence: 99%

“…[6][7][8]. The work in this paper is the continuation of the work presented in [8], which has followed the Lagrangian bird modelling approach and has employed viscous hourglass control to prevent excessive mesh distortion. It is computationally the most expensive hourglass control and is suitable in high rate dynamic and large deformation simulations [9].…”

Section: Introductionmentioning

confidence: 96%

“…As to improve the damage prediction procedure presented in [8] and increase analysis stability, in this work the Coupled Eulerian Lagrangian (CEL) capability of Abaqus/Explicit was utilized. The great advantage of CEL analyses is that all numerical difficulties associated with extreme bird mesh distortion are eliminated, as the Eulerian description allows finite elements to be fixed in space while the material flows through these elements.…”

Section: Introductionmentioning

confidence: 99%

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Bird strike damage analysis in aircraft structures using Abaqus/Explicit and coupled Eulerian Lagrangian approach

Smojver

Ivančević

2011

Composites Science and Technology

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a b s t r a c tThe subject of this paper is numerical prediction of bird strike induced damage in real aeronautical structures using highly detailed finite element models and modern numerical approaches. Due to the complexity of today's aeronautical structures, numerical damage prediction methods have to be able to take into account various failure and degradation models of different materials. A continuum damage mechanics approach has been employed to simulate failure initiation and damage evolution in unidirectional composite laminates. Hashin's failure initiation criteria have been employed in order to be able to distinct between four ply failure modes. The problem of soft body impacts has been tackled by applying the Coupled Eulerian Lagrangian technique, thereby avoiding numerical difficulties associated with extensive mesh distortion. This improvement in impactor deformation modelling resulted in a more realistic behaviour of bird material during impact. Numerical geometrical and material nonlinear transient dynamic analyses have been performed using Abaqus/Explicit. The main focus of the work presented in this paper is the application of the damage prediction procedure in damage assessment of bird impact on a typical large airliner inboard flap structure. Due to the high cost of gas-gun testing of aircraft components, experimental testing on the real flap structure could not have been performed. In order to evaluate the accuracy of the presented method, the bird and composite damage model have been validated against experimental data available in the literature.

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Section: Discussionmentioning

confidence: 99%

Section: Validation Of Cel Bird Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

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Bird strike damage analysis in aircraft structures using Abaqus/Explicit and coupled Eulerian Lagrangian approach

Smojver

Ivančević

2011

Composites Science and Technology

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“…Anisotropic composites (Chaudhuri and Balaraman, 2007; Czig any and De ak, 2012; M esz aros et al, 2013) are often utilized in air-, spacecraft (Smojver and Ivan cevi c, 2010;Ivan cevi c and Smojver, 2011; Ivan cevi c, 2011, 2012;Langdon et al, 2014) and sport industry (Jiang, 2014;Li and Jing, 2014;Su, 2014;Zhang, 2014;Tang, 2014), composite panels are also applied in cars and vehicles (Norhidayah et al, 2014;Wennberg and Stichel, 2014;Khan et al, 2014), ships (Chirica et al, 2011;Chirica, 2013), pressure vessels (Gheshlaghi et al, 2006 and many other engineering applications (Goch et al, 2012). The mechanical behavior of laminated composite plates and shells can be described by different theories.…”

Section: Introductionmentioning

confidence: 99%

Nonsingular crack modelling in orthotropic plates by four equivalent single layers

Szekrényes

2016

European Journal of Mechanics - A/Solids

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Keywords:Delamination Mixed mode II/III fracture Energy release rate Second-order plate theory Theoreom of autocontinuity Q3 a b s t r a c tIn this work the second-and third-order laminated plate theories are applied to model delaminated composite plates with material orthotropy. The method of four equivalent single layers is proposed and a general third-order displacement field is utilized in each layer. The kinematic continuity between the layers is established by the system of exact kinematic conditions. Apart from the continuity of the inplane displacements between the interfaces of the layers even the continuity of shear strains, their derivatives and curvatures is imposed. As a novelty a so-called shear strain control condition is introduced, which means that the shear strains at two or more points located along the thickness are imposed to be the same. Using the proposed conditions the equilibrium equations are derived for the delaminated and undelaminated regions of the plate. Plates with different boundary conditions are solved as examples and the theorem of autocontinuity is introduced, which is essentially related to the continuity conditions between the delaminated and undelaminated parts. The stress and displacement fields as well as the J-integral are determined in the examples and compared to finite element calculations. The results indicate that the control condition works very well in the case of the second-order plate theory, in contrast it is rather a disadvantage in the case of the third-order approximation.© 2015 Published by Elsevier Masson SAS. IntroductionAnisotropic composites (Chaudhuri and Balaraman, 2007; Czig any and De ak, 2012; M esz aros et al., 2013) are often utilized in air-, spacecraft (Smojver and Ivan cevi c, 2010;Ivan cevi c and Smojver, 2011; Ivan cevi c, 2011, 2012;Langdon et al., 2014) and sport industry (Jiang, 2014;Li and Jing, 2014;Su, 2014;Zhang, 2014;Tang, 2014), composite panels are also applied in cars and vehicles (Norhidayah et al., 2014;Wennberg and Stichel, 2014;Khan et al., 2014), ships (Chirica et al., 2011;Chirica, 2013), pressure vessels (Gheshlaghi et al., 2006 and many other engineering applications (Goch et al., 2012). The mechanical behavior of laminated composite plates and shells can be described by different theories. The classical laminated plate theory (CLPT) is based on the Kirchhoff assumption and so, it does not take the shear deformation into account (Radosavljevi c and Dra zi c, 2010;Eftekhari and Jafari, 2012;Hajheidari and Mirdamadi, 2013). The first-order shear deformation (FSDT or Mindlin) theory assumes constant shear strain distribution over the thickness of the plate (Kreja and Schmidt, 2006;Endo and Kimura, 2007;Assie et al., 2012;Batista, 2012;Nanda and Sahu, 2012;Sabik and Kreja, 2013;Endo, 2015). As a next step, the second-order plate theory (SSDT) proposes that the in-plane displacements are captured by quadratic functions in terms of the through-thickness coordinate (Baddour, 2011;Izadi and Tahani, 2010;Shahrjerdi et al., 2011...

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Multiscale Modeling of Composite Materials: a Roadmap Towards Virtual Testing

et al. 2011

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A bottom-up, multiscale modeling approach is presented to carry out high-fidelity virtual mechanical tests of composite materials and structures. The strategy begins with the in situ measurement of the matrix and interface mechanical properties at the nanometer-micrometer range to build up a ladder of the numerical simulations, which take into account the relevant deformation and failure mechanisms at different length scales relevant to individual plies, laminates and components. The main features of each simulation step and the information transferred between length scales are described in detail as well as the current limitations and the areas for further development. Finally, the roadmap for the extension of the current strategy to include functional properties and processing into the simulation scheme is delineated.

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Numerical simulation of bird strike damage prediction in airplane flap structure

Cited by 68 publications

References 9 publications

Bird strike damage analysis in aircraft structures using Abaqus/Explicit and coupled Eulerian Lagrangian approach

Bird strike damage analysis in aircraft structures using Abaqus/Explicit and coupled Eulerian Lagrangian approach

Nonsingular crack modelling in orthotropic plates by four equivalent single layers

Multiscale Modeling of Composite Materials: a Roadmap Towards Virtual Testing

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