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

Riccio, Aniello; Saputo, Salvatore; Sellitto, Andrea; Russo, Angela; Caprio, Francesco Di; Palma, Luigi Di

doi:10.3390/aerospace6060072

Cited by 32 publications

(11 citation statements)

References 30 publications

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“…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%

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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Section: Sph-fem Computational Modelmentioning

confidence: 99%

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

2019

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“…Several uncertainties, in terms of boundary conditions, impact velocity, etc. [13,14], can often affect test results.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Crashworthiness Study of a Full-Scale Composite Fuselage Section

Caputo¹,

Lamanna²,

Perfetto³

et al. 2021

AIAA Journal

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This work deals with the development of an improved numerical model, based on the explicit finite element method, aimed at investigating the energy absorption capabilities of a full-scale composite fuselage section of a regional aircraft and the related biomechanical injuries affecting the passengers. The experiment, conducted within the Italian national research project named "Innovative and Advanced Verification and Certification methods," consisted in a drop test of a fully equipped barrel performed at the Italian Aerospace Research Centre, according to the special conditions of the Federal Aviation Regulation Certification Specification 25. From a free-fall height of about 4 m, a ground contact impact velocity of 9.14 m∕s was measured. The numerical model has been developed faithfully to the experiment. Numerical analysis results, in terms of global deformations, failures, local accelerations, and biomechanical injuries, have been compared with the experimental ones to assess the prediction capability of the proposed numerical modeling procedure with a focus on improved crashworthy components for certification by analysis future purpose.

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“…The mechanism can be studied, though for specific geometries, by finite element simulation of impulsive loads on structures. 5 Impact and penetration analysis are essential for many engineering applications such as crash testing of structures and materials, [6][7][8][9] surface investigation, installing deep sea anchors, foundations. 10 Many aspects of impact mechanics have been addressed in recent literature.…”

Section: Introductionmentioning

confidence: 99%

Effects of spinning on residual velocity of ogive-nosed projectile undergoing ordnance velocity impact

Pranay

Panigrahi

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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In the present article, finite element analysis (FEA) based simulation on the study of the impact of projectiles having ogive nose shape has been made using ANSYS explicit dynamics. The effects of spinning on the residual velocity of ogive nosed projectile undergoing ordnance velocity impact have been presented. The variations of residual velocity due to different projectile materials and target plate thickness have been evaluated when the projectile is impacted by translational and spinning velocity. The target plates and ogive nosed projectile of a given material are discretized, and a rigorous error and convergence study has been made. Subsequently, the residual velocity of the considered model is evaluated by numerical techniques based on FEA. The results with the optimized meshed model are compared with the analytical results using the penetration theory and found that the results are well compared. Parametric study of the residual velocity has been made with varied ogive nosed materials and target plate thickness when the ogive nosed projectile undergoing ordnance velocity impact. Based on the numerical results, it has been found that the ogive nose projectile having tungsten alloy material is more effective undergoing ordnance velocity impact compared to steel 4340 material. For a given target plate thickness, spinning velocity, and impact velocity, the residual velocity is about 3 percent higher for the projectile made up of tungsten alloy compared to the steel 4340. The effects of the target plate thickness on the residual velocity of the ogive nose projectile do not seem to have much significant effects. It may be due to the simple reason that the ratio of the target plate thickness to projectile diameter is remaining within the intermediate range, i.e. within 1 and 10.

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

Cited by 32 publications

References 30 publications

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

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

Experimental and Numerical Crashworthiness Study of a Full-Scale Composite Fuselage Section

Effects of spinning on residual velocity of ogive-nosed projectile undergoing ordnance velocity impact

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