Crashworthiness of wing leading edges under bird impact event

Caprio, Francesco Di; Cristillo, D.; Saputo, Salvatore; Guida, Michele; Riccio, Aniello

doi:10.1016/j.compstruct.2019.02.069

Cited by 45 publications

(26 citation statements)

References 17 publications

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“…Dealing with the impact damage of composite laminates, the continuum damage mechanics (CDM) can well describe the intra-laminar damage [36] and have been widely adopted [7,33,37,38] in the framework of finite element method (FEM). The square laminate was modelled by CDM in present study.…”

Section: Numerical Modelmentioning

confidence: 99%

“…Bird-strike impacts are the major cause of blade damage for aircraft engines [1]. Therefore, the bird-induced failure of both fan blades [2][3][4][5] and leading edges [6][7][8][9][10][11] have caused much research interest. The latest bird-strike example was an Airbus A321 of Russian Ural Airlines on 15 August 2019, which was struck by birds during take-off, and subsequently its dual engines failed.…”

Section: Introductionmentioning

confidence: 99%

“…Guida et al [6] hybridized carbon fiber reinforced plastic laminates with shape memory alloy materials and showed better impact properties of the laminates containing the hybrid layers. Di Caprio et al [7] considered the bird-strike crashworthiness of different material systems (different stacking sequences and total thicknesses), without changing the overall geometrical shape. Liu et al [19] experimentally studied the damage of hygrothermally conditioned carbon epoxy composites under high-velocity impact.…”

Section: Introductionmentioning

confidence: 99%

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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%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Bird-Strike Resistance of Composite Laminates with Different Materials

2019

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“…Mohagheghian et al (Mohagheghian et al, 2017) performed the laboratory-scale impact experiments using a gas gun apparatus for betterquantified understanding of soft impact damage on laminated glass windows and more effective design of aircraft windshields. Di Caprio et al (Di Caprio, Cristillo, Saputo, Guida, & Riccio, 2019) assessed the bird-strike numerical models by a double-checked and hence the two test cases considered procedure: 1) bird strike on the flat square plate; 2) bird strike on the wing leading edge. These results indicate that the most damaged region in bird-strike tests are always the impact contact area.…”

Section: Introductionmentioning

confidence: 99%

Impact responses of slender composite plates for bird-strike testing of fan blades

Zhou

Sun

Huang

2019

Lat. Am. j. solids struct.

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Bird-strike failure of fan blades is one of the basic challenges for the safety of aircraft engines. Simplified slender blade-like plates are always used to evaluate the impact-induced damage mechanism at design stage. One undesirable issue is the failure at the root of clamped slender plates, which cannot recover the real case of twisted blades. For this purpose, three different strategies were exploited to obtain desirable deformation and stress responses, namely the impact location, additional weight, and the boundary condition. Numerical models of the simplified slender blade and the bird projectile were constructed by using finite element method (FEM) and smoothed particle hydrodynamics (SPH) approaches. The impact deformations and stress distributions were comparatively investigated in detail. The numerical results show that changing the boundary condition is the most effective way to obtain preferable impact responses for further failure analysis of real fan blades. Present results will be useful to future experimental design of simplified bird-strike testing.

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“…Orlando et al [33] studied a composite flap configuration compliant with EASA and FAA bird strike requirements. Di Caprio et al [34] considered the unidirectional fiber-reinforced composite material systems of wing leading edges, for the outer and inner faces of the skins under a bird impact event, with various skin thicknesses considered. According to the airworthiness requirements, Guida et al [35] adapted an innovative layup on an aeronautical structure, which was subjected to the bird strike phenomenon at 180 m/s and with an impacting mass of 1.8 kg.…”

Section: Introductionmentioning

confidence: 99%

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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Crashworthiness of wing leading edges under bird impact event

Cited by 45 publications

References 17 publications

Bird-Strike Resistance of Composite Laminates with Different Materials

Bird-Strike Resistance of Composite Laminates with Different Materials

Impact responses of slender composite plates for bird-strike testing of fan blades

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

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