@techreport{oai:jaxa.repo.nii.ac.jp:00044829,
 author = {野原, 利雄 and NOHARA, Toshio},
 month = {Jun},
 note = {The airworthiness requirements demand, that transport aircraft structures should be designed, taking into consideration the fail-safe concept;namely, that the structure can still withstand a prescribed load regardless of significant damege. It is essential that the damage can be detected during regular inspections before it reaches a critical level. Thus, a thorough knowledge of crack propagation and residual strength characteristics of structures is required to meet the criteria of the fail-safe design. The present paper gives some results of crack propagation computations for stiffened panels, using unstiffened panel data and acounting for the stress intensity factor of unstiffened panel and stiffened panel. Fatigue crack growth rates were measured in fatigue tests of stiffened panels, with riveted and bonded stiffeners. The predicted crack growth rates of stiffened panels, calculated by using the stress intensity factor, were compared with experimental data. The experimental results show that the fatigue life of the panel with the bonded stiffeners was considerably longer than that of the panel with the riveted stiffeners. The predicted crack growth rates were in comparatively, good agreement with experimental data., 資料番号: NALTR0575000, レポート番号: NAL TR-575},
 title = {補強平板の疲れき裂進展の挙動について(第一報)},
 year = {1979}
}