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Sudden bending of cracked laminates
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Chen, E. P. Sih, G. C. |
| Copyright Year | 1980 |
| Description | A dynamic approximate laminated plate theory is developed with emphasis placed on obtaining effective solution for the crack configuration where the 1/square root of r stress singularity and the condition of plane strain are preserved. The radial distance r is measured from the crack edge. The results obtained show that the crack moment intensity tends to decrease as the crack length to laminate plate thickness is increased. Hence, a laminated plate has the desirable feature of stabilizing a through crack as it increases its length at constant load. Also, the level of the average load intensity transmitted to a through crack can be reduced by making the inner layers to be stiffer than the outer layers. The present theory, although approximate, is useful for analyzing laminate failure to crack propagation under dynamic load conditions. |
| File Size | 2336727 |
| Page Count | 54 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800016888 |
| Archival Resource Key | ark:/13960/t7dr7nw06 |
| Language | English |
| Publisher Date | 1980-02-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Thickness Plate Theory Cracks Stress Analysis Bending Moments Failure Analysis Stiffness Dynamic Loads Laminates Elastodynamics Crack Propagation 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 |
