Introduction

  • René Alderliesten
Chapter
Part of the Solid Mechanics and Its Applications book series (SMIA, volume 236)

Abstract

Historically, Fibre Metal Laminates were introduced as a laminated material concept to improve the fatigue and damage tolerance properties of metallic structures in aeronautics. However, the concept can be viewed from different perspectives. This chapter discusses that the FML concept can be seen either as reinforcement of metallic structures or as reinforcement of fibre-reinforced polymer composite structures. Cases are given to illustrate how the concept of damage tolerance can be exploited with FMLs, in particular if the concept is viewed as structural concept rather than a material concept.

Keywords

Fatigue Titanium Magnesium Milling Ductility 

References

  1. 1.
    Vlot A (2001) GLARE—history of the development of a new aircraft material. Kluwer Academic Publishers, Dordrecht, The NetherlandsGoogle Scholar
  2. 2.
    Marissen R (1988) Fatigue crack growth in ARALL, a hybrid Aluminium-Aramid composite material, crack growth mechanisms and quantitative predictions of the crack growth rate. PhD Dissertation, Delft University of TechnologyGoogle Scholar
  3. 3.
    Roebroeks GHJJ (1991) Towards GLARE—the development of a fatigue insensitive and damage tolerant aircraft material. PhD Thesis, Delft University of Technology, DelftGoogle Scholar
  4. 4.
    Vlot A (2000) Towards technology readiness of fibre metal laminates—GLARE technology development 1997–2000. In: Proceedings of the 22nd international congress of aeronautical sciences, Harrogate, United Kingdom, 1–15Google Scholar
  5. 5.
    Kuang KSC, Kenny R, Whelan MP, Cantwell WJ, Chalker PR (2001) Residual strain measurement and impact response of optical fibre Bragg grating sensors in fibre metal laminates. Smart Mater Struct 10:338–346CrossRefGoogle Scholar
  6. 6.
    Austin TSP, Singh MM, Gregson PJ, Powell PM (2008) Characterisation of fatigue crack growth and related damage mechanisms in FRP–metal hybrid laminates. Compos Sci Technol 68:1399–1412CrossRefGoogle Scholar
  7. 7.
    Cortes P, Cantwell WJ (2006) The fracture properties of a fibre–metal laminate based on magnesium alloy. Compos B 37:163–170CrossRefGoogle Scholar
  8. 8.
    Alderliesten R, Rans C, Benedictus R (2008) The applicability of magnesium based fibre metal laminates in aerospace structures. Compos Sci Technol 68(14):2983–2993CrossRefGoogle Scholar
  9. 9.
    Burianek DA, Spearing SM (2002) Fatigue damage in titanium-graphite hybrid laminates. Compos Sci Technol 62:607–617CrossRefGoogle Scholar
  10. 10.
    Reyes G, Cantwell WJ (2000) The mechanical properties of fibre-metal laminates based on glass fibre reinforced polypropylene. Compos Sci Technol 60(7):1085–1094CrossRefGoogle Scholar
  11. 11.
    Carrillo JG, Cantwell WJ (2009) Mechanical properties of a novel fiber-metal laminate based on a polypropylene composite. Mech Mater 41(7):828–838CrossRefGoogle Scholar
  12. 12.
    Jensen BJ, Cano RJ, Hales SJ, Alexa JA, Weiser ES, Loos AC, Johnson WS (2009) Fiber Metal Laminates made by the VARTM process. In: Proceedings of the ICCM-17 conference, Edinburgh, ScotlandGoogle Scholar
  13. 13.
    Department of Defence (2005) Technology readiness assessment (TRA) deskbook. Director, Research Directorate (DRD), Office of the Director, Defense Research and Engineering (DDR&E), USAGoogle Scholar

Copyright information

© Springer International Publishing AG 2017

Authors and Affiliations

  • René Alderliesten
    • 1
  1. 1.Faculty of Aerospace EngineeringDelft University of TechnologyDelftThe Netherlands

Personalised recommendations