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Stress concentration around a small circular hole in the himat composite plate
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ko, W. L. |
| Copyright Year | 1985 |
| Description | Anisotropic plate theory is used to calculate the anisotropic stress concentration factors for a composite plate (AS/3501-5 graphite/epoxy composite, single ply or laminated) containing a circular hole. This composite material is used on the highly maneuverable aircraft technology (HiMAT) vehicle. It is found that the anisotropic stress concentration factor could be greater or less than 3 (the stress concentration factor for isotropic materials), and that the locations of the maximum tangential stress points could shift with the change of fiber orientation with respect to the loading axis. The effect of hole size on the stress concentration factor is examined using the Point Stress Criterion and the Averaged Stress Criterion. The predicted stress concentration factors based on the two theories compared fairly well with the measured values for the hole size 0.3175 cm (1/8 in). It is also found that through the lamination process, the stress concentration factor could be reduced drastically, indicating an improvement in structural performance. |
| File Size | 580352 |
| Page Count | 19 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860005880 |
| Archival Resource Key | ark:/13960/t0tr0sh3h |
| Language | English |
| Publisher Date | 1985-12-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Stress Concentration Tangents Anisotropic Plates Hole Geometry Mechanics Hole Distribution Mechanics Laminates Holes Mechanics Plates Structural Members Graphite-epoxy Composites Fiber Orientation Highly Maneuverable Aircraft Loads Forces Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |