Analysis of fuselage skin reinforcements with beam element models in flexible aircraft panels for ditching simulations

This paper is dedicated to the use of beam element models for skin structural reinforcements in guided ditching simulations with a flexible aircraft panel. approach was analysed by means finite structure subjected constant pressure load and loading conditions. To verify this approach, different discretization types mesh sizes were considered computations. Moreover, enhanced comparisons coupled Finite Element-Smoothed Particle Hydrodynamics Arbitrary Lagrangian Eulerian methods.