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Test and Modelling of Impact on Pre-Loaded Composite Panels

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Abstract

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.

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Authors and Affiliations

  1. Institute for Aircraft Design, University of Stuttgart, Stuttgart, Germany

    A. K. Pickett

  2. School of Applied Science, Cranfield University, Bedfordshire, UK

    M. R. C. Fouinneteau

  3. EADS, Ottobrunn, Germany

    P. Middendorf

Authors
  1. A. K. Pickett
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  2. M. R. C. Fouinneteau
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  3. P. Middendorf
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Correspondence to A. K. Pickett.

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Pickett, A.K., Fouinneteau, M.R.C. & Middendorf, P. Test and Modelling of Impact on Pre-Loaded Composite Panels. Appl Compos Mater 16, 225–244 (2009). https://doi.org/10.1007/s10443-009-9089-3

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  • DOI: https://doi.org/10.1007/s10443-009-9089-3

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