| タイトル | Analysis of matrix cracking and local delamination in (0/theta/-theta)sub s graphite epoxy laminates under tension load |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910013071 |
| 著者（英） | Salpekar, S. A.; Obrien, T. K. |
| 著者所属（英） | NASA Langley Research Center|Army Aviation Systems Command |
| 発行日 | 1991-03-01 |
| 言語 | eng |
| 内容記述 | Several 3D finite element analyses of (0/theta/-theta)sub s graphite epoxy laminates, where theta=15, 20, 25, 30, and 45 deg, subjected to axial tension load were performed. The interlaminar stresses in the theta/-theta interface were calculated with and without a matrix crack in the central -theta plies. The interlaminar normal stress changes from a small compressive stress when no matrix crack is present to a high tensile stress at the intersection of the matrix crack and free edge. The analysis of local delamination from the -theta matrix crack indicates a high strain energy release rate and a localized mode I component near the free edge, within one ply distance from the matrix crack. In order to examine the stress state causing the matrix cracking the maximum principal normal stress in a plane perpendicular to the fiber direction in the -theta ply was calculated in an uncracked laminate. The corresponding shear stress parallel to the fiber was also calculated. The principal normal stress at the laminate edge increases through the ply thickness and reached a very high tensile value at the theta/-theta interface indicating that the crack in the -theta ply may initiate at the theta/-theta interface. Crack profiles on the laminate edge in the -theta ply were constructed from the principal stress directions. The cracks were found to be more curved for layups with smaller theta angles, which is consistent with experimental observations in the literature. |
| NASA分類 | COMPOSITE MATERIALS |
| レポートNO | 91N22384
AVSCOM-TR-91-B-002
NAS 1.15:104062
NASA-TM-104062 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/132878 |
