Abstract
A three-dimensional elasticity solution of infinitely long, laminated anisotropic cylindrical panels with simply supported boundary condition is presented. Using exact three-dimensional equations, the resulting three highly coupled partial differential equations can be reduced to ordinary differential equations by choosing the solution composed of trigonometric functions along the circumferential direction. Numerical examples are presented for three stacking sequences (1) [θ̄°/90°] (2) [θ̄°/-θ̄°] (3) [θ̄°/-θ̄°/θ̄°] under transverse sinusoidal loading. The discussion is focused on the behavior of transverse normal stress. In general, the behavior is entirely different from that of laminated plates. The sign of transverse normal stress changes through the shell thickness. The slope of the transverse normal stress is generally not continuous across the interface of the laminate. The thickness and stacking sequence studied in the research do not change the distribution shape of transverse normal stress too much.
| Original language | English |
|---|---|
| Pages (from-to) | 728-738 |
| Number of pages | 11 |
| Journal | International SAMPE Symposium and Exhibition (Proceedings) |
| Volume | 38 |
| Issue number | 1 |
| Publication status | Published - 1993 Dec 1 |
| Event | Proceedings of the 1993 38th International SAMPE Symposium and Exhibition. Part 2 (of 2) - Anaheim, CA, USA Duration: 1993 May 10 → 1993 May 13 |
All Science Journal Classification (ASJC) codes
- Materials Science(all)
- Mechanics of Materials
- Mechanical Engineering