Advanced modelling of bird strike on high lift devices using hybrid Eulerian–Lagrangian formulation

Smojver, Ivica; Ivančević, Darko

doi:10.1016/j.ast.2011.07.010

Cited by 33 publications

(12 citation statements)

References 14 publications

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“…Common forms of EoS that are extensively adopted include Polynomial, Mie-Grüneisen and Murnaghan forms. A good agreement from simulations where the gelatine projectiles were modelled using the EoS, with theoretical and experimental shock pressure-time history curves has been reported (Smojver and Ivančević 2012).…”

Section: Introductionsupporting

confidence: 52%

“…A simple elastic-plastic material law developed by Stoll et al (Stoll and Brockman 1997) was used extensively to model the bird, but fluid-like flow response cannot be obtained with such a law unless a low shear modulus is set. The Equation of State (EoS) constitutive model is now commonly adopted as the material model of the bird impactor (Smojver and Ivančević 2010a;Smojver and Ivan 2009;Smojver and Ivančević 2012) and it is defined as the relationship between the projectile pressure and corresponding volume at room temperature, with the density of the projectile close to that of water. Common forms of EoS that are extensively adopted include Polynomial, Mie-Grüneisen and Murnaghan forms.…”

Section: Introductionmentioning

confidence: 99%

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Experimental and numerical investigation of high velocity soft impact loading on aircraft materials

Zhou

Liu

Zhang

et al. 2019

Aerospace Science and Technology

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Bird strike on aircraft remains a serious threat to flight safety. Experimental investigations employing real birds are associated with high cost and low reproducibility. Therefore, physical substitute materials are often used instead of real birds. This study investigates the soft impact loading on aluminium and laminated glass targets from ballistic gelatine and rubber projectiles. The two targets simulate strike on the aircrafts' fuselage and windshield respectively. The full field out of plane displacements of the targets were recorded for velocities 110 to 170 m s-1 using digital image correlation during gas gun experiments. A simulation model based on Smoothed Particle Hydrodynamics was developed and validated against the experimental data from all four projectile-target material combinations. It was shown that for the same momentum, a rubber projectile exerts a higher pressure on a target as compared to gelatine, even though the out of plane displacements and in-plane strains are similar. This led to fractures in the impacted laminated glass when rubber was used. The study offers new experimental data as well as efficient design modelling tools to mitigate damage imposed during bird strike. The models provide a way towards enabling the optimisation of real, large scale aircraft structures and components.

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Section: Introductionsupporting

confidence: 52%

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of high velocity soft impact loading on aircraft materials

Zhou

Liu

Zhang

et al. 2019

Aerospace Science and Technology

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“…A sixth-order Runge-Kutta timemarching forward algorithm has been developed, which fully integrates the nonlinear dynamical equations described in Eq. (20). The direct time-integration scheme is used to compute the values of Xt and Zt at each time step.…”

Section: Transient Response Of Rotating Airfoil Blades Due To Birmentioning

confidence: 99%

Transient Response of a Multilayered Composite Rotating Airfoil Under Slicing-Impact Loading

Sinha¹

2014

AIAA Journal

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In this paper, a semiclosed form of numerical solution is obtained for a slicing-impact edge loading on a multilayered composite airfoil. The analytical derivation of the governing partial differential equation simulates the transient event of the slicing process by considering the moving bird in the form of a soft-body impactor as it comes into contact with the rotating fan blades modeled as prestressed airfoil due to centrifugal force field. The oblique-impact formulation of a composite pretwisted fan blade includes the effect of both the contact-impact loads as well as the Coriolis forces. The consideration of coupled longitudinal-transverse elastic wave propagation in a rotating coordinate system is a key to correctly predict the impact response of a blade mounted on a rotor shaft. The dynamic loading on the airfoil and its transient response produced during the bird strike is determined by solving the coupled nonlinear dynamical equations governing the movement of the bird slice in the time domain using a sixth-order Runge-Kutta technique. Nomenclature A = cross-sectional area of the composite airfoil B D , B L = diameter and length of the cylinder representing the bird B M = mass of the incoming bird in the shape of a cylinder B m = mass of the single bird slice impacting on individual blade b = base radial distance of the blade root at the clamped end C = C 0 C 0 x, chord width of the airfoil at any span height x C 0 = C L − C 0 ∕L, rate of change of chord width from root to tip C = velocity-dependent matrix of composite airfoil c = chordwise instantaneous location of the traveling bird slice at any time t D 11 , D 22 , D 12 , D 66 = orthotropic flexural rigidity terms for the multilayered composite airfoil E xx , E yy = equivalent Young's modulus of elasticity of the composite airfoil material in the local x (span) and y (chord) directions, respectively ê t ;ê a ;ê r = unit vectors in the coordinate system attached to the rotating shaft ê x ;ê y ;ê z = unit vectors attached to the local airfoil span, chord, and normal directions ft Bird-slice = dynamic load being applied by the bird slice on the airfoil f impulse = time-dependent load on the blade leading edge during bird-slicing action f travel = time-dependent load on the blade during slice travel across the chord f cf = centrifugal forces on the blade acting radially outward fftg = external force column vector G xy , G yz , G zx = directional shear moduli in the bulk orthotropic blade material h = thickness of the airfoil blade î;ĵ;k = unit vectors in the global rectangular Cartesian coordinates (fixed in space) K = structural stiffness matrix of airfoil (functions of E xx , E yy , ν xy , G yz , h, etc.) K Ω = stiffness matrix due to centrifugal effect (functions of Ω, ρ, h, R, L, etc.) L = spanwise length of the airfoil along its stacking axis M = mass matrix of airfoil (functions of ρ, h, C, L, etc.) N b= number of blades on the fan rotor n1, n2 = number of terms in the deformation shape function Q x , Q y = shear forces per unit length at the x and ...

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“…Several researchers have addressed the subject of bird strike on composite structures using the Lagrangian, [5][6][7] Eulerian, [7][8][9] or SPH approaches. In the Lagrangian approach, a typical Lagrangian finite element mesh is used for the bird simulation.…”

Section: Introductionmentioning

confidence: 99%

“…This method does not present the mesh problems of other techniques; however, the modelling procedure is more complex and could potentially lead to more computationally expensive simulations. Several researchers have addressed the subject of bird strike on composite structures using the Lagrangian, [5][6][7] Eulerian, [7][8][9] or SPH approaches. 6,[10][11][12] Laminated composite structures are well known for their high strength to weight ratios, compared to traditional materials and are widely incorporated in several engineering applications.…”

Section: Introductionmentioning

confidence: 99%

Investigation of bird strike events on composite wing panels

Diamantakos

Fotopoulos

Jamin³

et al. 2017

Fatigue Fract Eng Mat Struct

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One of the most important events during an aircraft's service life is the impact of a bird (ie, bird strike), which could possibly lead to catastrophic failure. According to airworthiness authorities, compliance of an aircraft structure to bird‐strike certification specifications can potentially be proved by simulation. In the present work, combined experimental and numerical investigations are performed, aiming to provide a validated numerical simulation tool for the certification of a composite leading edge structure. To increase the numerical simulation efficiency, the stacked shell approach in the frame of the finite element method is adopted. Comparison of numerical and experimental results shows that the proposed methodology is very promising for the simulation of impact events on complex composite structures. The proposed methodology has been applied for the development of a numerical tool for the simulation of bird strike on a composite leading edge structure.

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Advanced modelling of bird strike on high lift devices using hybrid Eulerian–Lagrangian formulation

Cited by 33 publications

References 14 publications

Experimental and numerical investigation of high velocity soft impact loading on aircraft materials

Experimental and numerical investigation of high velocity soft impact loading on aircraft materials

Transient Response of a Multilayered Composite Rotating Airfoil Under Slicing-Impact Loading

Investigation of bird strike events on composite wing panels

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