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Postbuckling delamination of a stiffened composite panel using finite element methods
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Natsiavas, S. Babcock, C. D. Knauss, W. G. |
| Copyright Year | 1987 |
| Description | A combined numerical and experimental study is carried out for the postbuckling behavior of a stiffened composite panel. The panel is rectangular and is subjected to static in-plane compression on two opposite edges to the collapse level. Nonlinear (large deflection) plate theory is employed, together with an experimentally based failure criterion. It is found that the stiffened composite panel can exhibit significant postbuckling strength. |
| File Size | 732352 |
| Page Count | 20 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880012714 |
| Archival Resource Key | ark:/13960/t5hb4157t |
| Language | English |
| Publisher Date | 1987-08-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Finite Element Method Panels Plate Theory Rectangles Compression Loads Delaminating Failure Modes Nonlinearity Stiffening Fracture Strength Composite Structures Buckling Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
