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Out-of-plane stresses in composite shell panels: Layerwise and elasticity solutions

Miri, A. K ; Sharif University of Technology

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  1. Type of Document: Article
  2. DOI: 10.1007/s00707-011-0471-5
  3. Abstract:
  4. Boundary-layer effects in lengthy cross-ply laminated circular cylindrical shell panels under uniform axial extension are investigated by two analytical solutions. First, Reddy's layerwise theory with state-space approach is utilized to determine the local interlaminar stresses. In this method, the general displacement field is discretized through the shell thickness by a linear shape function. When the shell panel is subjected to an axial force, the axial strain is estimated by an equivalent single-layer theory. Second, the stress-function approach along with Fourier series expansion is applied to develop a novel elasticity solution. The elasticity solution, which is based on simply-support edge conditions, is presented to show the effectiveness of the first solution. The numerical results show good agreements. Interlaminar stresses within various symmetric and unsymmetric cross-ply composite shell panels are then calculated and discussed. It is shown that the normal out-of-plane stress can get high magnitudes along the physical interfaces
  5. Keywords:
  6. Analytical solutions ; Axial forces ; Axial strain ; Circular cylindrical shells ; Composite shell ; Cross-ply ; Displacement field ; Edge conditions ; Elasticity solutions ; Equivalent single layers ; Fourier-series expansion ; Interlaminar stress ; Layer-wise ; Layer-wise theory ; Numerical results ; Out-of-plane ; Physical interface ; Shape functions ; Shell thickness ; State space approach ; Elasticity ; Fourier analysis ; Fourier series ; Shells (structures) ; Nanocomposite films
  7. Source: Acta Mechanica ; Volume 220, Issue 1-4 , 2011 , Pages 15-32 ; 00015970 (ISSN)
  8. URL: http://link.springer.com/article/10.1007%2Fs00707-011-0471-5