| タイトル | The influence of lay-up and thickness on composite impact damage and compression strength |
| 著者（英） | Obrien, T. K.; Guynn, E. G. |
| 著者所属（英） | Kentron International, Inc.|Army Aviation Research and Development Command|NASA Langley Research Center |
| 発行日 | 1985-01-01 |
| 言語 | eng |
| 内容記述 | The effects of composite stacking sequence, thickness, and percentage of zero-degree plies on the size, shape, and distribution of delamination through the laminate thickness and on residual compression strength following impact were studied. Graphite/epoxy laminates were impacted with an 0.5 inch diameter aluminum sphere at a specific low or high velocity. Impact damage was measured nondestructively by ultrasonic C-scans and X-radiography and destructively by the deply technique, and compression strength tests were performed. It was found that differences in compression failure strain due to stacking sequence were small, while laminates with very low percentages of zero-degree plies had similar failure loads but higher failure strains than laminates with higher percentages of zero-degree plies. Failure strain did not correlate with planar impact damage area, and delaminations in impact regions were associated with matrix cracking. |
| NASA分類 | COMPOSITE MATERIALS |
| レポートNO | 85A30246
AIAA PAPER 85-0646 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/392092 |
|
