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Sudden stretching of a four layered composite plate
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Chen, E. P. Sih, G. C. |
| Copyright Year | 1980 |
| Description | An approximate theory of laminated plates is developed by assuming that the extensioral and thickness mode of vibration are coupled. The mixed boundary value crack problem of a four layered composite plate is solved. Dynamic stress intensity factors for a crack subjected to suddenly applied stress are found to vary as a function of time and depend on the material properties of the laminate. Stress intensification in the region near the crack front can be reduced by having the shear modulus of the inner layers to be larger than that of the outer layers. |
| File Size | 1750064 |
| Page Count | 43 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800016887 |
| Archival Resource Key | ark:/13960/t5s80600j |
| Language | English |
| Publisher Date | 1980-03-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Thickness Plate Theory Cracks Stress Analysis Boundary Value Problems Integral Equations Differential Equations Composite Structures Elastodynamics Computer Programs 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 |
