Abstract
Formulations and computational procedures are presented for the finite element analysis of laminated anisotropic composite thin shells including imperfections. The derivations of the nonlinear geometric element stiffness matrices were based on the total Lagrangian description. A 48 degree-of-freedom (d.o.f.) general curved shell element with arbitrary distribution of curvatures was used to model the shell middle- surface. Numerical results include the large deflection behavior of a variety of perfect plate and shell examples; buckling of a spherical shell with an axially symmetric im perfection ; and buckling of a cylindrical panel using measured initial transverse im perfections. A good comparison with existing results is obtained.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 197-214 |
| Number of pages | 18 |
| Journal | Journal of Composite Materials |
| Volume | 20 |
| Issue number | 2 |
| DOIs | |
| State | Published - Mar 1986 |
| Externally published | Yes |
All Science Journal Classification (ASJC) codes
- Ceramics and Composites
- Mechanics of Materials
- Mechanical Engineering
- Materials Chemistry