Mathematical and computer simulation of the response of aircraft composite elements to impact loading

Abstract

The present work suggests an analytical approach to investigating vibrations of laminated orthotropic elements of aircraft structures under impact by hail. The aircraft elements as non-closed cylindrical shells with a complicated form in the plan view are considered. Impact loading of a shell is carried out by an indenter, which is dropped on the shell from a certain height. The dynamic behaviour of the shells is described by the first-order theory accounting for transverse shear strain, thickness reduction and normal element rotation inertia in each layer. The method potentialities are demonstrated by calculating stresses in three-layer and five-layer orthotropic shells with different boundary conditions. A good match of results obtained by different methods confirms the feasibility and effectiveness of the method offered.