The relation of crack propagation behaviour and delamination on Fibre Acrylic Laminates under various cyclic conditions

Authors

  • Anindito Purnowidodo Brawijaya University Malang Jalan. Mayjend Haryono, 167, Malang, Indonesia, 65145, Indonesia
  • Khairul Anam Brawijaya University Malang Jalan. Mayjend Haryono, 167, Malang, Indonesia, 65145, Indonesia https://orcid.org/0000-0002-8588-9528
  • Bagus Maulidika Brawijaya University Malang Jalan. Mayjend Haryono, 167, Malang, Indonesia, 65145, Indonesia

DOI:

https://doi.org/10.15587/1729-4061.2018.139219

Keywords:

Crack propagation, delamination, cyclic conditions, Fibre Acrylic Laminates

Abstract

The investigation of the crack propagation behaviour associating with the delamination in the interface of the laminate of the fibre acrylic laminates (FALs) composite is carried out by subjecting the composite to cyclic loads. The cyclic load is controlled by the displacement provided by a fatigue testing machine. The cyclic load was carried out with various displacement ratios, R, values, these are, 0, –1, –3, and –5 in which the displacement amplitude was also varied as high as 0.15, 0.20, 0.30 mm, for every value of R. In the present study, the investigation to the crack propagation behaviour is focused on the negative cyclic of R leading to the composite to be cycled under compressive load. The results obtained in the present study shows that in these cases of the lower value of the displacement ratio of –3 and –5, the fatigue life and the crack length of the FALs increase, and the increasing of the displacement amplitude to 0.30 mm causes both the fatigue life and the crack length to be shorter. The delamination propagation rate is higher in the R=0 case than those in the negative value of R. In addition, the lateral contraction of material to outward over the crack region may contribute to the development of the delamination when the ratio of the displacement cycles is negative, and the lateral contraction is higher when the displacement ratio is more negative. Moreover, the delamination may take place in front of the crack tip when the maximum displacement is 0.20 mm or higher, and it causes the crack propagation to be accelerated

Author Biographies

Anindito Purnowidodo, Brawijaya University Malang Jalan. Mayjend Haryono, 167, Malang, Indonesia, 65145

Doctor of Technical Sciences, Associate Professor

Department of Mechanical Engineering

Khairul Anam, Brawijaya University Malang Jalan. Mayjend Haryono, 167, Malang, Indonesia, 65145

Lecturer

Department of Mechanical Engineering

Bagus Maulidika, Brawijaya University Malang Jalan. Mayjend Haryono, 167, Malang, Indonesia, 65145

Undergraduate Student

Department of Mechanical Engineering

References

  1. Callister, Jr. W. D., Retwisch, D. G. (2008). Introduction in Fundamentals of Materials Science and Engineering, An Integrated Approach. Ch. 1. New Jersey: John Wiley & Sons, Inc., 5–10.
  2. Alderliesten, R., Crack, F. (2005). Propagation and Delamination Growth in Glare. Delft, Netherland: DUP Science, 1–4.
  3. Jones, R. M. (1999). Introduction to Composite Materials-Mechanics of Composites Materials. Philadelphia, Taylor & Francis, 11–15.
  4. Khan, S. U., Alderliesten, R. C., Benedictus, R. (2011). Delamination in Fiber Metal Laminates (GLARE) during fatigue crack growth under variable amplitude loading. International Journal of Fatigue, 33 (9), 1292–1303. doi: https://doi.org/10.1016/j.ijfatigue.2011.04.002
  5. Huang, Y., Liu, J., Huang, X., Zhang, J., Yue, G. (2015). Delamination and fatigue crack growth behavior in Fiber Metal Laminates (Glare) under single overloads. International Journal of Fatigue, 78, 53–60. doi: https://doi.org/10.1016/j.ijfatigue.2015.04.002
  6. Dadej, K., Bieniaś, J., Surowska, B. (2017). Residual fatigue life of carbon fibre aluminium laminates. International Journal of Fatigue, 100, 94–104. doi: https://doi.org/10.1016/j.ijfatigue.2017.03.026
  7. Jones, R., Kinloch, A. J., Hu, W. (2016). Cyclic-fatigue crack growth in composite and adhesively-bonded structures: The FAA slow crack growth approach to certification and the problem of similitude. International Journal of Fatigue, 88, 10–18. doi: https://doi.org/10.1016/j.ijfatigue.2016.03.008
  8. Nojavan, S., Schesser, D., Yang, Q. D. (2016). A two-dimensional in situ fatigue cohesive zone model for crack propagation in composites under cyclic loading. International Journal of Fatigue, 82, 449–461. doi: https://doi.org/10.1016/j.ijfatigue.2015.08.029
  9. D’Amore, A., Giorgio, M., Grassia, L. (2015). Modeling the residual strength of carbon fiber reinforced composites subjected to cyclic loading. International Journal of Fatigue, 78, 31–37. doi: https://doi.org/10.1016/j.ijfatigue.2015.03.012
  10. Zhang, J., Peng, L., Zhao, L., Fei, B. (2012). Fatigue delamination growth rates and thresholds of composite laminates under mixed mode loading. International Journal of Fatigue, 40, 7–15. doi: https://doi.org/10.1016/j.ijfatigue.2012.01.008
  11. Bizeul, M., Bouvet, C., Barrau, J. J., Cuenca, R. (2010). Influence of woven ply degradation on fatigue crack growth in thin notched composites under tensile loading. International Journal of Fatigue, 32 (1), 60–65. doi: https://doi.org/10.1007/bf02670759
  12. Bao, H., McEvily, A. J. (1995). The effect of an overload on the rate of fatigue crack propagation under plane stress conditions. Metallurgical and Materials Transactions A, 26 (7), 1725–1733. doi: https://doi.org/10.1007/bf02670759
  13. McEvily, A. J., Yang, Z. (1990). The nature of the two opening levels following an overload in fatigue crack growth. Metallurgical Transactions A, 21 (10), 2717–2727. doi: https://doi.org/10.1007/bf02646067
  14. Makabe, C., Purnowidodo, A., Miyazaki, T., McEvily Arthur, J. (2005). Deceleration and acceleration of crack propagation after an overloading under negative baseline stress ratio. Journal Testing and Evaluation, 33 (5), 181–187.
  15. Makabe, C., Purnowidodo, A., McEvily, A. J. (2004). Effects of surface deformation and crack closure on fatigue crack propagation after overloading and under loading. International Journal of Fatigue, 26 (12), 1341–1348. doi: https://doi.org/10.1016/j.ijfatigue.2004.03.017
  16. Pumowidodo, A., Miyazaki, T., Makabe, C., McEvily, A. J. (2004). Transitional Behavior of Residual Fatigue Life After Applying Overload During Fatigue Crack Growth With Constant Stress Amplitude. Pressure Vessel and Piping Codes and Standards, 39–44. doi: https://doi.org/10.1115/pvp2004-2671
  17. Barsom, J. M., Rofle, S. T. (1999). Stress Analysis for Members with Crack. Fracture and fatigue control in structure. 3rd ed. Philadelphia: ASTM.
  18. Purnowidodo, A., Anam, K., Wahyudi, A., Arief, S. (2014). The Effect of Stop Holes Technique on Crack Growth Behaviours Emanating From a Notch after Overloading. International Journal of Applied Engineering Research, 9 (1), 125–136.
  19. Topper, T. H., Lam, T. S. (2003). Derivation of crack closure and effective fatigue crack growth data from smooth specimen fatigue test. Report of Fatigue Branch of The Society of Materials Science Japan, 266, 1–12.
  20. Ward-Close, C. M., Blom, A. F., Ritchie, R. O. (1989). Mechanisms associated with transient fatigue crack growth under variable-amplitude loading: An experimental and numerical study. Engineering Fracture Mechanics, 32 (4), 613–638. doi: https://doi.org/10.1016/0013-7944(89)90195-1
  21. Sadananda, K. (1999). Analysis of overload effects and related phenomena. International Journal of Fatigue, 21, 233–246. doi: https://doi.org/10.1016/s0142-1123(99)00094-8
  22. Mitchell, M. R., Link, R. E., Purnowidodo, A., Fukuzato, S., Saimoto, A., Makabe, C. (2007). Crack Growth Behavior in Overloaded Specimens with Sharp Notch in Low Carbon Steel. Journal of Testing and Evaluation, 35 (5), 100097. doi: https://doi.org/10.1520/jte100097

Downloads

Published

2018-08-21

How to Cite

Purnowidodo, A., Anam, K., & Maulidika, B. (2018). The relation of crack propagation behaviour and delamination on Fibre Acrylic Laminates under various cyclic conditions. Eastern-European Journal of Enterprise Technologies, 4(12 (94), 6–15. https://doi.org/10.15587/1729-4061.2018.139219

Issue

Vol. 4 No. 12 (94) (2018): Materials Science

Section

Materials Science

License

Copyright (c) 2018 Anindito Purnowidodo, Khairul Anam, Bagus Maulidika

Creative Commons License

This work is licensed under a Creative Commons Attribution 4.0 International License.

The consolidation and conditions for the transfer of copyright (identification of authorship) is carried out in the License Agreement. In particular, the authors reserve the right to the authorship of their manuscript and transfer the first publication of this work to the journal under the terms of the Creative Commons CC BY license. At the same time, they have the right to conclude on their own additional agreements concerning the non-exclusive distribution of the work in the form in which it was published by this journal, but provided that the link to the first publication of the article in this journal is preserved.

A license agreement is a document in which the author warrants that he/she owns all copyright for the work (manuscript, article, etc.).
The authors, signing the License Agreement with TECHNOLOGY CENTER PC, have all rights to the further use of their work, provided that they link to our edition in which the work was published.
According to the terms of the License Agreement, the Publisher TECHNOLOGY CENTER PC does not take away your copyrights and receives permission from the authors to use and dissemination of the publication through the world's scientific resources (own electronic resources, scientometric databases, repositories, libraries, etc.).
In the absence of a signed License Agreement or in the absence of this agreement of identifiers allowing to identify the identity of the author, the editors have no right to work with the manuscript.
It is important to remember that there is another type of agreement between authors and publishers – when copyright is transferred from the authors to the publisher. In this case, the authors lose ownership of their work and may not use it in any way.