Impacts on fuselages: a trial in using numerical simulation to predict residual strength
Résumé
Quasi-static and dynamic characterization tests laminates have been carried out on balanced angle ply [±θ] and used for calibration of numerical values of different models derived to predict damage initiation and growth in aeronautical large structures. Impact induced damage from experiment’s measures and numerical predictions are compared for T800/M21S aeronautical samples impacted at 15J.