Modelling of Bird Strike on an Aircraft Wing Leading Edge Made from Fibre Metal Laminates – Part 1: Material Modelling
Source abstract
Abstract
Fibre Metal Laminates with layers of aluminium alloy and high strength glass fibre composite have been reported to possess excellent impact properties and be suitable for aircraft parts likely to be subjected to impacts from objects such as runway debris or birds. In a collaborative research project, aircraft wing leading edge structures with a glass-based FML skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this first part of a two-part paper, a material model developed for FML suitable for use in impact modelling with explicit finite element analysis is presented. The material model is based on a recent implementation in the commercial finite element code PAM-CRASH/SHOCK of a Continuum Damage Mechanics (CDM) model for composites, incorporating anisotropic strain rate effects. Results from the model are compared with experimental results on FML at variable strain rates and the model is shown to be capable of capturing most of the complex strain rate dependent behaviour exhibited by these materials.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: High-Velocity Impact and Material Behavior · Mechanical Behavior of Composites · Structural Response to Dynamic Loads
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References (30)
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1. Cleary, E. C., Dolbeer, R. A. and Wright, S. E., 'Wildlife Strikes to Civil Aircraft in the United States 1990-2002', Serial Report Number 9, Federal Aviation Administration, Office of Airport Safety and Standards, Washington, DC, 2003.
2. Vlot, A., 'Impact Loading on Fibre Metal Laminates', International Journal of Impact Engineering 18(3), 1996, 291–307.10.1016/0734-743X(96)89050-6 ↗
3. Vlot, A., Vogelesang, L. B. and deVries, T. J., 'Towards Application of Fibre Metal Laminates in Large Aircraft', Aircraft Engineering and Aerospace Technology 71(6), 1999, 558–570.10.1108/00022669910303711 ↗
4. Vogelesang, L. B. and Vlot, A., 'Development of Fibre Metal Laminates for Advanced Aerospace Structures', Journal of Materials Processing Technology 103, 2000, 1–5.10.1016/S0924-0136(00)00411-8 ↗
5. Vlot, A., 'Low-Velocity Impact Loading on Fibre Reinforced Aluminium Laminates (ARALL) and Other Aircraft Sheet Materials', Dissertation, Delft University of Technology, 1991.
6. Vlot, A., 'Impact Properties of Fibre Metal Laminates', Composites Engineering 3, 1993, 911–927.10.1016/0961-9526(93)90001-Z ↗
7. Vlot, A. and Fredell, R. S., 'Impact Damage Resistance and Damage Tolerance of Fibre Metal Laminates', in Proceedings of the ICCM/9 Madrid, Vol. VI, 1993, pp. 51–58.
8. Vlot, A., Bulters, P. B. M. and Fredell, R. S., 'Low and High Velocity Impact Loading on Fibre/Metal Laminates, Carbon/PEEK and Monolithic Aluminium 2024-T3', in Advanced Materials and Structures from Research to Application, European Chapter, J. Brandt, H. Hornfield and M. Neitzel (eds), SAMPE, 1992, pp. 347–360.
9. CRAHVI: Crashworthiness of Aircraft for High Velocity Impact, CEC DG XII Competitive and Sustainable Growth Project GRD1-2000-25242, 2000-2004.
10. Petrinic, N., 'High Strain Rate Mechanical Properties of GLARE', CRAHVI Deliverable Report D1.1.8, University of Oxford, UK, September 2002.
11. Vlot, A., High Strain Rate Tests on Fibre Metal Laminates, Series 07, Delft University Press, The Netherlands, 1998.
12. Burstow, C. G., Lovell, M. C. and Rodgers, A. L., 'Mechanisms of Dislocation Motion in 7075-T73 Aluminium Alloy at Strain Rates Round 105 s-1', in Mechanical Properties of Materials at High Rates of Strain, Proceedings of the Fourth International Conference on the Mechanical Properties at High Rates of Strain, Oxford, 1989, pp. 317–322.
13. Kawata, K., Hashimoto, S., Sekino, S. and Takeda, N., 'Macro-and Micro-Mechanics of High-Velocity Brittleness and High-Velocity Ductility of Solids', in Macro-and Micro-Mechanics of High Velocity Deformation and Fracture, Proceedings of the IUTAM Symposium, K. Kawata and J. Shioriri (eds), Springer-Verlag, Japan, 1985.
14. Davies, R. G. and Magee, C. L., 'The Effect of Strain-Rate Upon the Tensile Deformation of Materials', Journal of Engineering Materials and Technology, 1975, 151–155.10.1115/1.3443275 ↗
15. Chao, T. T. and Moore, R. L., 'Strain Rate Effect on the Ultimate Tensile Stress of Fibre Epoxy Strands', in Carbon Reinforced Epoxy Systems, C. J. Hilado (ed.), Technomic Press, 1974, p. 1–4.
16. Harding, J. and Welsh, J., 'A Tensile Testing Technique for Fibre-Reinforced Composites at Impact Rates of Strain', Journal of Materials Science 18, 1983, 1810–1826.10.1007/BF00542078 ↗
17. Chiem, C. Y. and Liu, Z. G., 'The Relationship Between Tensile Strength and Shear Strength in Composite Materials Subjected to High Strain Rates', Journal of Engineering Materials and Technology 110, 1988, 191–194.10.1115/1.3226030 ↗
18. Thiruppukuzhi, S. V. and Sun, C. T., 'Models for the Strain-Rate-Dependent Behavior of Polymer Composites', Composites Science and Technology 61, 2001, 1–12.10.1016/S0266-3538(00)00133-0 ↗
19. PAM-SHOCK(tm)/PAM-CRASH(tm) FE Code. Engineering Systems International, F-94578 Rungis Cedex, France.
20. Lee, H. T. and Shaue, G. H., 'The Thermomechanical Behaviour for Aluminium Alloy under Uniaxial Tensile Loading', Materials Science and Engineerin g A268, 1999, 154–164.10.1016/S0921-5093(99)00069-6 ↗
21. McCarthy, M. A. and Wiggenraad, J. F. M., 'Numerical Investigation of a Crash Test of a Composite Helicopter Subfloor Structure', Composite Structures 51, 2001, 345–359.10.1016/S0263-8223(00)00150-1 ↗
22. Lee, J.W., Allen, D. H. and Harris, C. E., 'Internal State Variable Approach for Predicting Stiffness Reductions in Fibrous Laminated Composites with Matrix Cracks', Journal of Composite Materials 23, 1989, 1273–1291.10.1177/002199838902301205 ↗
23. Coats, T. W. and Harris, C. E., 'A Progressive Damage Methodology for Residual Strength Predictions of Notched Composite Panels', National Aeronautics and Space Administration Technical Memorandum 1998-207646.
24. Kumar, R. S. and Talreja, R., 'A Continuum Damage Model for Linear Viscoelastic Composite Materials', Mechanics of Materials 35, 2003, 463–480.10.1016/S0167-6636(02)00265-X ↗
25. Hashagen, F. and de Borst, R., 'Enhancement of the Hoffman Yield Criterion with an Anisotropic Hardening Model', Computers & Structures 79, 2001, 637–651.10.1016/S0045-7949(00)00164-4 ↗
26. Schipperen, J. H. A., 'An Anisotropic Damage Model for the Description of Transverse Matrix Cracking in a Graphite-Epoxy Laminate', Composite Structures 53, 2001, 295–299.10.1016/S0263-8223(01)00013-7 ↗
27. Ladeveze, P. and Le Dantec, E., 'Damage Modelling of the Element Ply for Laminated Composites', Composites Science and Technology 43, 1992, 257–267.10.1016/0266-3538(92)90097-M ↗
28. Soden, P. D., Hinton, M. J. and Kaddour, A. S., 'Lamina Properties, Lay-Up Configurations and Loading Conditions for a Range of Fibre-Reinforced Composite Laminates', Composites Science and Technology 58, 1998, 1011–1022.10.1016/S0266-3538(98)00078-5 ↗
29. Engineered Materials Handbook, Vol. 1 : Composites, ASM International, Metals Park, Ohio, 1987.
30. Rozycki, P., 'Contribution au développement de lois de comportement pour matériaux composites soumis à l'impact', Thèse de Doctorat, Université de Valenciennes et du Hainaut-Cambrésis, 2000.