Numerical methodologies for simulating bird-strike on composite wings

Riccio, Aniello; Cristiano, Roberta; Saputo, Salvatore; Sellitto, Andrea

doi:10.1016/j.compstruct.2018.03.018

Cited by 42 publications

(27 citation statements)

References 66 publications

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“…At high velocities, the bird projectile behaves like fluidic materials, and its inhomogeneity becomes negligible and hence can be treated as "soft body" [29,30]. The hydrodynamic responses of fluidic materials can be accurately modelled by the smoothed particle hydrodynamics (SPH) method, which has experienced wide use in bird-strike simulations [2,25,29,[31][32][33][34]. In the present simulation study with ABAQUS software, the bird projectile was firstly meshed by finite elements (C3D8R), and then they were converted to SPH particles (PC3D) at the beginning of the bird-impact analysis (time threshold = 0).…”

Section: Numerical Modelmentioning

confidence: 99%

Bird-Strike Resistance of Composite Laminates with Different Materials

2019

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To obtain some basic laws for bird-strike resistance of composite materials in aeronautical application, the high-velocity impact behaviors of composite laminates with different materials were studied by numerical methods. The smoothed particle hydrodynamics (SPH) and finite element method (FEM) coupling models were validated from various perspectives, and the numerical results were comparatively investigated. Results show that the different composite materials have relatively little effect on projectile deformations during the bird impact. However, the impact-damage distributions can be significantly different for different composite materials. The strength parameters and fracture energy parameters play different roles in different damage modes. Lastly, modal frequency was tentatively used to explain the damage behavior of the composite laminates, for it can manifest the mass and stiffness characteristics of a dynamic structure. The dynamic properties and strength properties jointly determine the impact-damage resistance of composite laminates under bird strike. Future optimization study can be considered from these two aspects.

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Section: Numerical Modelmentioning

confidence: 99%

Bird-Strike Resistance of Composite Laminates with Different Materials

2019

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“…Among these methods, SPH can better describe bird fragmentation into discrete particles with high efficiency. Therefore, SPH has recently experienced high popularity [2,5,10,15,16,32,33,40,41] in bird strike, high-velocity impact, and other large deformation studies. In the present study, a SPH method was employed, represented by a set of discrete but interacting particles, which belong to a meshless particle-based method.…”

Section: Sph-fem Computational Modelmentioning

confidence: 99%

“…For convenience in studying the damage evolution, we decided to use a square plate. The impact damage of composite laminates can be efficiently modelled by means of the finite element method (FEM) [19,32,42]. For the fiber breakage and matrix cracking simulation, continuum damage mechanics (CDM) enables one to predict with fine accuracy the onset and growth of damages, by introducing degradation factors for the material properties d f , d m and d s for fiber, matrix and shear modes, respectively.…”

Section: Sph-fem Computational Modelmentioning

confidence: 99%

“…Recently, Mohagheghian et al [16] found that the polymer interlayer type had the most significant effect on both deformations and failure modes of the laminated glass windows at room temperature. Riccio et al [32] analysed the state-of-the-art formulations for the bird and composite wing modelling in detail, providing discussion on the added value and the weak points. Orlando et al [33] studied a composite flap configuration compliant with EASA and FAA bird strike requirements.…”

Section: Introductionmentioning

confidence: 99%

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SPH-FEM Design of Laminated Plies under Bird-Strike Impact

2019

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Composite laminates can potentially reduce the weight of aircrafts; however, they are subjected to bird strike hazards in civil aviation. To handle their nonlinear dynamic behaviour, in this study, the impact damage of composite laminates were numerically evaluated and designed by means of smoothed particle hydrodynamics (SPH) and the finite element method (FEM) to simulate the interaction between bird projectiles and the laminates. Attention was mainly focused on the different damage modes in various laminates’ plies induced by bird impact on a square laminated plate. A continuum damage mechanics approach was exploited to simulate damage initiation and evolution in composite laminates. Damage maps were computed with respect to different ply angles, i.e., 0°, 45° and −45°. The damage distributions were comparatively investigated, and then the ply design was considered for crashworthiness improvement. The results aim to serve as a design guideline for future prototype-scale bird strike studies of complex laminated structures.

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“…The increasing use of civil aircraft transport requires more and more attention to aircraft design to ensure occupant safety and structural integrity by means of controlled kinetic energy absorption, ensuring a level of deceleration within a given threshold [1][2][3][4] under an impact event. This design approach, also known as the crashworthiness design, is deeply influenced by the geometrical conditions, impact parameters, and material interactions [5,6] related to the impact phenomena's great complexity [7][8][9][10]. In order to design a structure capable of absorbing the impact load transmitted between the ground and the fuselage, guaranteeing a satisfactory level of occupant safety in accordance with the Federal Aviation Administration (FAA) standards [1], several robust numerical models have been developed in order to reduce the costly experimental tests, which are often affected by uncertainty due to boundary conditions, such as the material characteristics, impact velocity, and actual dimensions [11].…”

Section: Introductionmentioning

confidence: 99%

An Insight on the Crashworthiness Behavior of a Full-Scale Composite Fuselage Section at Different Impact Angles

et al. 2019

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In the present paper, advanced numerical methodologies have been adopted to investigate the influence of impact angle on the crashworthiness behavior of a composite fuselage section. The analyzed fuselage section, made of unidirectional fiber-reinforced material, woven fabric material, and aluminum material, is representative of a regional aircraft fuselage. Two different angles of impact with rigid ground have been investigated and reported: Perpendicularly to the ground and with a pitch angle of 3 degrees with respect to the ground. The adopted numerical models have been preliminarily validated with experimental data from a drop test on a full-scale fuselage section, in terms of deformations and failure location and progression. The correlation between the numerical model and the experimental test has enabled evaluation of the effect of the impact angle on the deformation and damage in the sub-cargo floor area.

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Numerical methodologies for simulating bird-strike on composite wings

Cited by 42 publications

References 66 publications

Bird-Strike Resistance of Composite Laminates with Different Materials

Bird-Strike Resistance of Composite Laminates with Different Materials

SPH-FEM Design of Laminated Plies under Bird-Strike Impact

An Insight on the Crashworthiness Behavior of a Full-Scale Composite Fuselage Section at Different Impact Angles

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