SPH – Lagrangian study of bird impact on leading edge wing

Guida, Michele; Marulo, Francesco; Meo, Michele; Grimaldi, Antonio; Olivares, Gerardo

doi:10.1016/j.compstruct.2010.10.001

Cited by 81 publications

(33 citation statements)

References 15 publications

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“…The results showed that the clamped boundary condition type increased target stiffness leading to increased energy absorption and delamination. Guida et al [18] also highlighted the influence of structural compliance during bird-strike testing and simulations based on a single bay section of a leading-edge fin tailcone. During the development of the simulations the authors included the supporting frame due to its potential influence on the impact measurements.…”

Section: Contents Lists Available At Sciencedirectmentioning

confidence: 98%

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

McCallum

2015

Materials & Design

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Section: Contents Lists Available At Sciencedirectmentioning

confidence: 98%

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

McCallum

2015

Materials & Design

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“…Most recently, Guida et al [9] used the Lagrange and SPH approaches to model the bird impact on LE bay in composite materials made of aluminium honeycomb core and GLARE cover plates. Excellent qualitative correlation between the numerical model and the experimental test was obtained in terms of global deformations mode.…”

Section: Introductionmentioning

confidence: 99%

Dynamic response of the leading edge wing under soft body impact

Zakir

2012

International Journal of Crashworthiness

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Soft body impact tests were conducted using an artificial bird of 0.2 kg with a striking velocity of 150 m·s −1 on three different configurations of metallic wing leading edge (LE) structures. The objective of these experiments is to address the preliminary design of LE wing structures to soft body impact loads. The explicit finite element software PAM-CRASH was selected to simulate these experiments using smoothed particle hydrodynamics (SPH) techniques for modelling the bird. The impact tests were also performed for a velocity of 70-180 m·s −1 on instrumented aluminium and steel flat plates to attain the bird material parameters. The artificial bird material parameters for a hydrodynamic material model (Murnaghan equation of state) and elastic-plastic solids with damage and failure were optimised using iSIGHT and PAM-CRASH coupling technique in conjunction with tests on flat plates. The experimental and numerical correlations of the flat plates suggested that at high velocity the hydrodynamic material model gives good results. Bird-strike simulations on wing LE structures were performed using optimised artificial bird parameters. The load transferred to the support structure and post-test deflection-simulated results showed good conformity with the experiment. The SPH method proved to be very effective for modelling a bird strike on flat plates and LE structures. The deformation behaviour of the SPH bird appears to be in excellent agreement with the video stills, with the flow around the structure and break-up into particles.

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“…Email: liyulong@nwpu.edu.cn large transport aircraft and a submodelling approach was used to reduce computational time. Guida et al [5] conducted bird-strike tests on a wing leading edge and developed a numerical method to optimise the design of the wing leading edge. In the numerical method, the classical finite element approach was adopted to model the wing leading edge while the SPH method was used for modelling the bird.…”

Section: Introductionmentioning

confidence: 99%

Dynamic response of bird strike on aluminium foam-based sandwich panels

Liu

Gao

et al. 2015

International Journal of Crashworthiness

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This study attempts to establish an experimentalÀnumerical framework to simulate the dynamic response of aluminium foam-based sandwich panels subjected to bird strike. The numerical model is developed with the non-linear dynamic finite element code PAM-CRASH, where the smooth particle hydrodynamics (SPH) algorithm is used to model the bird, an elasticÀplastic material model with isotropic damage is used to describe aluminium skin and the DeshpandeÀFleck foam model is used to describe the foam core. Mechanical tests of the skin and foam materials as well as bird-strike tests of a double sandwich panel are conducted and the experimental results are used to calibrate the model parameters. The birdstrike simulation results show reasonably good agreement with test data, indicating the simulation method is capable of predicting the dynamic response of aluminium foam-based sandwich panels in the event of bird strike. Finally a series of parametric studies are conducted to examine the effects of foam thickness and arrangement on the deformation behaviour and energy-absorbing ability of the sandwich panels to illustrate the potential application of the numerical model in the design of aluminium foam-based sandwich structures.

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SPH – Lagrangian study of bird impact on leading edge wing

Cited by 81 publications

References 15 publications

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

The influence of preload and boundary conditions on pre-damaged composite plates subject to soft-body impact

Dynamic response of the leading edge wing under soft body impact

Dynamic response of bird strike on aluminium foam-based sandwich panels

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