Analysis of composite stiffener under successive impact and bending test
Source abstract
Abstract
In this article, we present the analysis, modelling and experimental investigation of composite omega stiffeners from non-penetrating impact to bending-after-impact. We used advanced computational methods to determine the extent of damage due to impact and, without many simplifications to the damage, predict the residual bending-after-impact strength under four-point-bend tests. The predicted sizes and patterns of impact damage, and the subsequent predicted bending strengths are compared to experimental tests of omega stiffeners. This work shows that preserving the details and fidelity of damage in the computational model is critical to successful prediction of residual strength. It was also found that modifying the design of the stiffeners by changing the orientation of some of the plies reduces the extent of impact damage and increases residual bending strength.
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Research context
OpenAlex topics: Mechanical Behavior of Composites · Structural Response to Dynamic Loads · High-Velocity Impact and Material Behavior
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
Affiliations
Department of Mechanical Engineering, National University of Singapore, Singapore
Airbus Operations GmbH, Department: ESCRBY Airframe Composite Fuselage R&T, Germany
Funding
Singapore Ministry of Education · AIRBUS Operations GmbH
References (32)
Show source-provided references
1. 10.1016/0263-8223(93)90015-I10.1016/0263-8223(93)90015-I ↗
2. 10.1177/00219983970310150110.1177/002199839703101501 ↗
3. 10.1016/0263-8223(88)90060-810.1016/0263-8223(88)90060-8 ↗
4. 10.1115/1.150484810.1115/1.1504848 ↗
5. ASTM D7136/D7136M-15 · 2015
6. ASTM D7137/D7137M-12 · 2012
7. AITM1-0010 · 2005
8. 10.1016/j.compositesb.2011.04.01710.1016/j.compositesb.2011.04.017 ↗
9. 10.1016/j.compscitech.2005.04.00910.1016/j.compscitech.2005.04.009 ↗
10. 10.1016/S0263-8223(98)00081-610.1016/S0263-8223(98)00081-6 ↗
11. 10.1016/j.paerosci.2015.11.00410.1016/j.paerosci.2015.11.004 ↗
12. 10.1016/j.compositesb.2014.07.01110.1016/j.compositesb.2014.07.011 ↗
13. 10.1016/j.compositesa.2013.08.00310.1016/j.compositesa.2013.08.003 ↗
14. Dost EF, Ilcewicz LB, Avery WB, et al. Effects of stacking sequence on impact damage resistance and residual strength for quasi-isotropic laminates. In: TK O'Brien (ed.) Composite Materials: Fatigue and Fracture (Third Volume) . Philadelphia: ASTM International, 1991. Available at: https://books.google.com.sg/books?id=oOWAnvkrD70C&printsec=frontcover#v=onepage&q&f=false.10.1520/STP17733S ↗
15. 10.1016/j.compstruct.2012.05.01510.1016/j.compstruct.2012.05.015 ↗
16. 10.1016/j.compositesa.2015.01.02510.1016/j.compositesa.2015.01.025 ↗
17. 10.1016/j.compositesb.2014.01.03310.1016/j.compositesb.2014.01.033 ↗
18. 10.1016/j.compscitech.2014.04.01510.1016/j.compscitech.2014.04.015 ↗
19. 10.1016/j.compstruct.2015.11.06010.1016/j.compstruct.2015.11.060 ↗
20. 10.1007/s10853-006-0208-310.1007/s10853-006-0208-3 ↗
21. 10.1007/s10443-013-9382-z10.1007/s10443-013-9382-z ↗
22. 10.1016/j.compositesa.2010.02.00510.1016/j.compositesa.2010.02.005 ↗
23. 10.1016/B978-0-08-100332-9.00018-910.1016/B978-0-08-100332-9.00018-9 ↗
24. 10.1016/j.compositesa.2013.11.01210.1016/j.compositesa.2013.11.012 ↗
25. 10.1016/j.compositesa.2012.12.00110.1016/j.compositesa.2012.12.001 ↗
26. 10.1016/j.compstruct.2014.12.02210.1016/j.compstruct.2014.12.022 ↗
27. 10.1177/00219983710050010610.1177/002199837100500106 ↗
28. 10.1016/0266-3538(96)00005-X10.1016/0266-3538(96)00005-X ↗
29. 10.1016/S0266-3538(96)00140-610.1016/S0266-3538(96)00140-6 ↗
30. 10.1016/S0266-3538(02)00125-210.1016/S0266-3538(02)00125-2 ↗
31. In: Werner S (ed). Carbon fiber reinforced plastics. Airbus material database. Hamburg, Airbus GmbH, 2015.
32. Abaqus analysis user's manual guide , Version 6.11, Providence: Dassault Systèmes, USA, 2012.