Applied Composite Materials

, Volume 18, Issue 1, pp 85–100

Analysis and Compression Testing of Laminates Optimised for Damage Tolerance



Barely Visible Impact Damage (BVID) can occur when laminated composite material is subject to out-of-plane impact loads and can result in a significant reduction in compressive strength. This paper reports on three compression tests of laminates optimised to maximise damage tolerance. Results from these tests were analysed using a semi-analytical, fracture mechanics based method that predicts the strain below which laminated coupons containing BVID subject to axial compression will not fail. A further experiment was conducted on an artificially delaminated coupon in order to validate the modelling methodology. Results from one of the two optimised stacking sequences considered show an increase of over 40% in Compression After Impact (CAI) strength compared with a baseline configuration. Analysis of results has indicated that CAI strength is dependent to a great extent on damage morphology and stability of damage growth, both of which are functions of laminate stacking sequence.


Static strength Delamination Compression Impact Damage tolerance 


  1. 1.
    Flanagan, G.: Two-dimensional delamination growth in composite laminates under compression loading. In Composite Materials: Testing and Design. In: Whitcomb JD (ed) ASTM STP 972. ASTM, Philadelphia, Ch. 8, 180–190 (1988)Google Scholar
  2. 2.
    Chai, H., Babcock, C.D.: Two-dimensional modelling of compressive failure in delaminated laminates. J. Comp. Mats. 19, 67–98 (1985)CrossRefGoogle Scholar
  3. 3.
    Rhead, A.T., Butler, R., Hunt, G.W.: Post-buckled propagation model for compressive fatigue of impact damaged laminates. Int. J. Sol. Struct. 45(16), 4349–4361 (2008)CrossRefGoogle Scholar
  4. 4.
    Rhead, A.T., Butler, R.: Compressive static strength model for impact damaged laminates. Compos. Sci. Technol. 69(14), 2301–2307 (2009)CrossRefGoogle Scholar
  5. 5.
    Rhead, A.T., Butler, R., Marchant, D.: Compressive strength of laminates following free edge impact. Comp. Part A. (2009). doi:10.10.16/j.compositesa.2009.10.024 article in press.
  6. 6.
    Chai, H., Babcock, C.D., Knauss, W.G.: One dimensional modelling of failure in laminated plates by delamination buckling. Int. J. Struct. 7(11), 1069–1083 (1981)CrossRefGoogle Scholar
  7. 7.
    Williams, F.W., Kennedy, D., Butler, R., Anderson, M.S.: VICONOPT—Program for exact vibration and buckling analysis or design of prismatic plate assemblies. AIAA 29(11), 1927–1928 (1991)CrossRefGoogle Scholar
  8. 8.
    Hwang, S.-F., Liu, G.-H.: Buckling behaviour of composite laminates with multiple delaminations under uniaxial compression. Compos. Struct. 53, 235–243 (2001)CrossRefGoogle Scholar
  9. 9.
    Hitchen, S.A., Kemp, R.M.J.: The effect of stacking sequence on impact damage in a carbon fibre/epoxy composite. Composites 26, 207–214 (1995)CrossRefGoogle Scholar
  10. 10.
    Baker, N., Rhead, A.T., Butler, R.: Optimisation of aerospace laminates for damage tolerance. 7th ASMO-UK/ISSMO International Conference of Engineering Design Optimisation, Bath (2008)Google Scholar
  11. 11.
    ASTM 2009 Standard test method for measuring the damage resistance of a fiber-reinforced polymer matrix composite to a drop-weight impact event, Designation: D7136 / D7136M - 07 doi:10.1520/D7136_D7136M-07

Copyright information

© Springer Science+Business Media B.V. 2010

Authors and Affiliations

  1. 1.Department of Mechanical EngineeringUniversity of BathBathUK

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