FATIGUE CRACK GROWTH IN ADHESIVELY BONDED STRUCTURES AND COMPOSITE REPAIRS

Since fatigue crack can initiate and grow with cyclic stress which is far below than its yield stress, it is a huge threat in aviation industry which can cost both life and financial loss. After 2009, the US Federal Aviation Administration requires composite and adhesively bonded structures on aircraft to be designed based on slow growth approach. This requirement allows delamination/disbond to grow during the designed life if the growing is slow, stable and predictable. This thesis aims to develop a methodology for predicting the growth of delamination/disbond in adhesively bonded structures and bonded repairs.