A method has been proposed to predict the fatigue life to the transverse crack initiation in cross-ply and quasi-isotropic carbon fiber reinforced plastic (CFRP) laminates. The six kinds of the laminates were formed of the two kinds of the prepregs, T800S/3900-2B with toughened interlaminar layers and T800H/3631 without toughened interlaminar layers. The unidirectional and cross-ply laminates of the stacking sequence of  12 , [0/90 4 ] S and [0/90 6 ] S were formed of the T800S/3900-2B prepreg, and the cross-ply and quasi-isotropic laminates of the stacking sequence of [0/90 2 ] S , [0/90 6 ] S and [45/0/-45/90] S were formed of T800H/3631 prepreg. Tensile fatigue tests were performed under load control using a hydraulic fatigue testing machine. The transverse crack initiation in the laminates under fatigue loading was evaluated by modifying the Smith-Watson-Topper (SWT) model, which can evaluate the mean stress effect on the fatigue life. Finally, it was found that the initiation of transverse crack in the laminates with the various laminate configuration can be predicted using the modified SWT model, and that means that it is possible to predict the initiation of transverse crack in the laminates with the various laminate configuration using S-N curve of unidirectional laminates in 90° direction.
|出版ステータス||Published - 2015 1月 1|
|イベント||34th Conference and the 28th Symposium of the International Committee on Aeronautical Fatigue and Structural Integrity, ICAF 2015 - Helsinki, Finland|
継続期間: 2015 6月 1 → 2015 6月 5
|Conference||34th Conference and the 28th Symposium of the International Committee on Aeronautical Fatigue and Structural Integrity, ICAF 2015|
|Period||15/6/1 → 15/6/5|
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