Journal of Mechanical Science and Technology

, Volume 19, Issue 4, pp 947–957 | Cite as

Modelling of low velocity impact damage in Laminated Composites



In this study a simple model is developed that predicts impact damage in a composite laminate avoiding the need of the time-consuming dynamic finite element method (FEM). The analytical model uses a non-linear approximation method (Rayleigh-Ritz) and the large deflection plate theory to predict the number of failed plies and damage area in a quasi-isotropic composite circular plate (axisymmetric problem) due to a point impact load at its centre. It is assumed that the deformation due to a static transverse load is similar to that oc curred in a low velocity impact. It is found that the model, despite its simplicity, is in good agreement with FEM predictions and experimental data for the deflection of the composite plate and gives a good estimate of the number of failed plies due to fibre breakage. The predicted damage zone could be used with a fracture mechanics model developed by the second investigator and co-workers to calculate the compression after impact strength of such laminates. This approach could save significant running time when compared to FEM solutions.

Key Words

Low Velocity Impact Model Non-linear Approximation Method Composite Laminate Compression After Impact Strength 


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Copyright information

© The Korean Society of Mechanical Engineers (KSME) 2005

Authors and Affiliations

  1. 1.Aerospace EngineeringThe University of SheffieldUK
  2. 2.Department of Aerospace EngineeringChosun UniversityGwangjuKorea

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