In-Plane Compressive Behaviour of Stiffened Thin-Skinned CFRP Panels with a Stress Concentrator  
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  Soutis-Fleck Fracture Model
  • The model was developed to predict the compressive failure strength of a multidirectional composite laminate with an open hole.
  • The model employs stress based and energy based techniques.
  • The model does not consider out of plane effects such as bending due to buckling.
  • Is valid when microbuckling of the 0° plies is expected.
  • Impact damage may be modelled by replacing it with an open hole of volume equivalent to the fibre breakage zone.
  • Microbuckling occurs in 0° plies subjected to compressive loading.
  • Microbuckling occurs at a point of stress concentration and extends perpendicular to the load.
  • Microbuckling occurs because the matrix is relatively compliant compared with the fibres.
In-Plane failure due to microbuckling of 0° plies. Out-of-plane failure due to buckling and delamination buckling.
 
     
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