Modelling Verification of an Airframe Section and Comparisons With Impact Test

Abstract The objective of this paper is to outline a model and solution for predicting the dynamic behaviour of a fuselage component under a survivable crash condition. The analytical approach reported here utilises the PAM-CRASH Finite Element (FE) software to model the structure of an aircraft subfloor fuselage component subjected to a normal bending impact load, i.e. belly landing condition. It is supported by a set of static and dynamic test programmes in order to establish the collapse mechanisms of various sections of a fuselage component. A series of parametric underfloor studies was performed for one of the dynamic tests modelled here to verify the results of the simulations with the dynamic test by taking into consideration the influence of modelling techniques. The work is part of a wider research project backed by the European Commission for identification of fuselage structural failure mechanism.