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A new merit function for evaluating the flaw tolerance of composite laminates. part 2; arbitrary size holes and center cracks (Document No: 20000017965)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sumpter, Rod Martin Jr., Mikulas M. |
| Copyright Year | 2000 |
| Description | In a previous paper, a new merit function for determining the strength performance of flawed composite laminates was presented. This previous analysis was restricted to circular hole flaws that were large enough that failure could be predicted using the laminate stress concentration factor. In this paper, the merit function is expanded to include the flaw cases of an arbitrary size circular hole or center crack. Failure prediction for these cases is determined using the point stress criterion. An example application of the merit function is included for a wide range of graphite/epoxy laminates. |
| File Size | 1126537 |
| Page Count | 46 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20000017965 |
| Archival Resource Key | ark:/13960/t47q3xk7m |
| Language | English |
| Publisher Date | 2000-01-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Stress Concentration Nondestructive Tests Cracks Failure Analysis Predictions Graphite-epoxy Composites Criteria Laminates Holes Mechanics Defects 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 |
