Abstract
Skin-stiffener structures are widely used for aerospace structures such as an airplane tail. It is well known that debondings often occur between the skin and stiffener. In order to assure the structural integrity, it is necessary to predict the debondings between them. In this study, a simulation method to predict the debondings for skin-stiffener structures is investigated. Laminated shell elements are adopted to achieve practical calculation time for large structures. The energy release rates at debonding fronts are calculate, and subsequent debonding is judged from the energy release rate. The process is repeated until given displacement is achieved. Analytical results of a beam type specimen are compared with a beam theory solution, and there are good agreements between them.
