Abstract
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.
Original language | English (US) |
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Pages (from-to) | 15-32 |
Number of pages | 18 |
Journal | Acta Mechanica |
Volume | 220 |
Issue number | 1-4 |
DOIs | |
State | Published - Aug 2011 |
Externally published | Yes |
All Science Journal Classification (ASJC) codes
- Computational Mechanics
- Mechanical Engineering