Numerical Study on Impact Response of Aircraft Sandwich Wing Made of Fiber-Metal Laminate Face-Sheets Subjected to Bird Strike

Abstract:

Aircraft structures are frequently subjected to impacts from objects such as runway debris and birds. In new aircraft structural design, Fiber Metal Laminates (FMLs) play a significant role due to their excellent mechanical properties, particularly the impact properties. In this study, the aircraft sandwich wing with FML face-sheets are analyzed by finite element model for simulating the bird strike. The numerical simulations of bird strike impact are performed adopting a lagrangian approach to design the wing by MSC/PATRAN FE code. The numerical obtained results are compared with the results in the literature for validation of the model. The effect of fiber orientations, fiber types, metal types in FML face sheets in sandwich wing on impact responses are investigated. The impact responses are illustrated by displacement history, contact force history and energy absorption. According to these results, the sandwich panel with FML skin is suitable structure for energy absorption (that is the most important factor in impact phenomena). The lay-ups with titanium metal layer with aramid fibers are the best.

• Periodical: Advanced Materials Research (Volumes 488-489)
• Pages: 8-13
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.488-489.8
• Online since: March 2012
• Authors: S.M.R. Khalili, M. Assar, R. Eslami Farsani, I. Hajiyousefi
• Keywords: Aircraft Wing Leading Edge, Bird Strike, Fiber-Metal Laminate (FML), Finite Element Analysis (FEA), Smooth Particle Hydrodynamics

References

[1] Federal Aviation Regulation FAR 33. 76. Bird ingestion. FAA, 2007. 9.

[2] Metrisin, J. and B. Potter (2001). Simulating Bird Strike Damage in Jet Engines,. ANSYS Solutions. Volume 3, Number 4. Pages 8-9.

[3] The permanent deformation of a cantilever strucks transversely at its. tip. Proc. Roy. Soc. Lond., England. Parkes, E, (1955).

[4] Stronge W.J. and T. Yu. (1993). Dynamic Models for Structural Plasticity,. Springer-Verlag, London, Great Britain.

[5] Goldsmith, W. (2001). IMPACT: The Theory and Phisical Behaviour of Colliding Solids ,. Dover Publications, Mineola, New York.

[6] Cassenti, B. N. (1979). Hugoniot Pressure Loading in Soft Body Impacts,. United Technologies Research Center, Connecticut.

[7] Barber, J. P., H. R. Taylor and J. S. Wilbeck (1975). Characterization of Bird Impacts on a Rigid Plate: Part 1,. Technical report AFFDL-TR-75-5.

DOI: 10.21236/ada021142

[8] Niering, E. (1988). Simulation of Bird Strikes on Turbine Engines , Turbinen-Union Munich, Germany.

[9] Moffat, T. J. and W. L. Cleghorn (2001). Prediction of Bird Impact Pressures and Damage using MSC/DYTRAN,. Proceedings of ASME TURBOEXPO 2001, Louisiana.

DOI: 10.1115/2001-gt-0280

[10] MSC. Dytran® User's Guide, Version 2010, chapter2, pp.2-4.

[11] Kistler LS, Waas AM. On the response of curved laminated panels subjected to transverse impact loads. International Journal of Solids Structure 1999; 36: 1311–27.

DOI: 10.1016/s0020-7683(98)00005-5

[12] Tarfaoui M , Gning PB, Hamitouche L. Dynamic response and damage modeling of glass/epoxy tubular structures: Numerical investigation. Composites: Part A 2008; 39: 1–12.

DOI: 10.1016/j.compositesa.2007.10.001

[13] C.J. Read. Standard test method for bird impact testing of aerospace transparent enclosures. ASTM F330-89, 2004. 8.

[14] Aviation Regulation Part 25, Air Worthiness standards: Transport category air planes , (2004).

[15] C.J. Read. Standard test method for bird impact testing of aerospace transparent enclosures. ASTM F330-89, 2004. 8.

[16] Information on http: /www. matbase. com/material/composites/fibermetallaminates-fml.

[17] MSC. Dytran® User's Guide, Version 2010, chapter1, pp.1-2.