A numerical model for bird strike of aluminium foam-based sandwich panels |
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| Affiliation: | 1. Structural Impact Laboratory (SIMLab), Department of Structural Engineering, Norwegian University of Science and Technology (NTNU), N-7491 Trondheim, Norway;2. SINTEF Materials Technology, Rich. Birkelandsvei 2B, N-7465 Trondheim, Norway;3. EADS CCR, quai Marcel Dassault – BP 76-92152 Suresnes Cedex, France;4. LSTC, 7374 Las Positas Road, Livermore, CA 94550, USA;1. School of Civil and Transportation Engineering, Guangdong University of Technology, Guangzhou 510006, China;2. Institute of Applied Mechanics and Biomedical Engineering, Taiyuan University of Technology, 79 West Yingze Street, Taiyuan 030024, China;3. State Key Laboratory of Traction Power, Southwest Jiaotong University, Chengdu 610031, China;4. School of Civil Engineering, Qinghai University, Xining 810016, China;1. State Key Laboratory of Structural Analysis for Industrial Equipment, Department of Engineering Mechanics, Dalian University of Technology, Dalian 116024, China;2. Ningbo Institute of Dalian University of Technology, Ningbo 315016, China;3. Department of Discipline Engineering, AVIC Commercial Aircraft Engine Co., LTD, Shanghai 200241, China;4. Shanghai Engineering Research Center of Civil Aero Engine, Shanghai 200241, China;5. School of Chemical Engineering, Dalian University of Technology, Dalian, Liaoning 116024, China Received 30 June 2020; revised 22 July 2020; accepted 31 August 2020 |
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| Abstract: | Experimental bird-strike tests have been carried out on double sandwich panels made from AlSi7Mg0.5 aluminium foam core and aluminium AA2024 T3 cover plates. The bird-strike velocity varied from 140 to 190 m/s. The test specimens were instrumented with strain gauges in the impacted area to measure the local strains of the rear sandwich plate. A numerical model of this problem has been developed with the non-linear, finite element program LS-DYNA. A continuum damage-mechanics-based constitutive model was used to describe the behaviour and failure of the aluminium cover plates. The foam core was modelled by a pressure sensitive constitutive model coupled by a failure criterion on maximum volumetric strains. The bird was represented by an idealised geometry and the material model was defined by a linear equation-of-state. A multi-material arbitrary Lagrangian Eulerian (ALE) element formulation was used to represent the motion of the bird, whereas the sandwich panel was described by a Lagrangian reference configuration. A fluid–structure interface ensured proper coupling between the motion of the bird and the solid materials of the sandwich panel. It was found that the model was able to represent failure of both the aluminium cover plates as well as the aluminium foam core. |
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