Non-linear analysis of tapered (in steps) laminated plate under uniform inplane load
Research output: Journal Publications and Reviews (RGC: 21, 22, 62) › 21_Publication in refereed journal › Not applicable › peer-review
Author(s)
Detail(s)
| Original language | English |
|---|---|
| Pages (from-to) | 205-223 |
| Journal / Publication | Composite Structures |
| Volume | 7 |
| Issue number | 3 |
| Publication status | Published - 1987 |
| Externally published | Yes |
Link(s)
Abstract
An initial stress iteration method using a quasi-three-dimensional element has been developed for the material non-linear analysis of Carbon Fibre Reinforced Plastic (CFRP) laminates of infinite width subjected to a uniform inplane load. Analyses of variable thickness (stepped) laminated plates with various arrangements for the ply fibre directions have been carried out. Linear and non-linear numerical results are given for a single step plate with resin layers included. The non-linear results show that peak stresses predicted by the linear analysis are reduced. This is a result of non-linear (plastic) deformation of the resin. A maximum strain failure criterion is used and failure modes of the free edge and stepped plate problems are predicted. The delaminating stress for the [90/90/90/90]s stepped plate compares well with experiments. © 1987.
Citation Format(s)
Non-linear analysis of tapered (in steps) laminated plate under uniform inplane load. / Wu, C. M L.
In: Composite Structures, Vol. 7, No. 3, 1987, p. 205-223.Research output: Journal Publications and Reviews (RGC: 21, 22, 62) › 21_Publication in refereed journal › Not applicable › peer-review
