NUMERICAL SIMULATION OF THE STRUCTURAL BEHAVIOUR OF ORTOTHROPICALLY STIFFENED AIRCRAFT PANELS UNDER SHORT TIME DURATION LOADING

摘要

This paper studies the structural behaviour by numerical simulation of ortothropically stiffened aircraft panels subjected to dynamic loading. Focus is placed on a stringer-frame stiffened circular aircraft fuselage panel loaded by different duration load pulses. The simulation of the behaviour under a static load through buckling and the post-buckling regime is presented. The panel's own dynamic characteristics are presented followed by the application of different time pulses. The results are compared to the base line static behaviour. Finally, a summary, conclusions and recommendations for future research are presented.