Applied Composite Materials

, Volume 16, Issue 4, pp 225–244

Test and Modelling of Impact on Pre-Loaded Composite Panels

  • A. K. Pickett
  • M. R. C. Fouinneteau
  • P. Middendorf

DOI: 10.1007/s10443-009-9089-3

Cite this article as:
Pickett, A.K., Fouinneteau, M.R.C. & Middendorf, P. Appl Compos Mater (2009) 16: 225. doi:10.1007/s10443-009-9089-3


Currently test and simulation of low and high speed impact of Aerospace composite structures is undertaken in an unloaded state. In reality this may not be the case and significant internal stresses could be present during an impact event such as bird strike during landing, or takeoff. In order to investigate the effects of internal loading on damage and failure of composite materials a series of experimental and simulation studies have been undertaken on three composite types having different fibres, resins and lay-ups. For each composite type panels have been manufactured and transversely impacted under the condition of ‘unloading’ or ‘pre-loading’. For preloading a rig has been constructed that can impose a constant in plane strain of up to 0.25% prior to impact. Results have clearly shown that preloading does lower the composite impact tolerance and change the observed failure modes. Simulation of experiments have also been conducted and have provided an encouraging agreement with test results in terms of both impact force time histories and prediction of the observed failure mechanisms.


A- carbon fibres B- impact behaviour C- damage mechanics D- finite element analysis E-failure criterion 

Copyright information

© Springer Science+Business Media B.V. 2009

Authors and Affiliations

  • A. K. Pickett
    • 1
  • M. R. C. Fouinneteau
    • 2
  • P. Middendorf
    • 3
  1. 1.Institute for Aircraft DesignUniversity of StuttgartStuttgartGermany
  2. 2.School of Applied ScienceCranfield UniversityBedfordshireUK
  3. 3.EADSOttobrunnGermany

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