Determination of a Load Approaches for Aircraft Impacts - The Risks of Nuclear Energy Technology - page 263

Fig. 14.10 Idealized bursting load and mass distributions of a Phantom (data corresponding to the
Sandia test)

Fig. 14.11 Sequence of nodal deformation (buckling) along the fuselage axis at t ¼ 1 ms,

t ¼ 30 ms and t ¼ 70 ms

others to examine the influence of impact projectiles filled with liquids
(cf. e.g. [ 23 ]). Using two aircraft models with chosen parameters as examples the
general behaviour is shown below, once using the long-range aircraft Boeing
747 and once using the typical medium-range aircraft Airbus 320.
For a description of the process the deformation of the aircraft on impact or
rather its step-by-step destruction is of interest. It is only in this matter that the
surface loading of an impacted structure with temporally fluctuating load distribu-
tions as well as the temporal difference of the impact of different aircraft compo-
nents can be determined. A computational analysis of the impact will be shown with
a two-dimensional aircraft model which takes into consideration the spatial distri-
bution of rigidity and mass as well as the destruction due to non-linear material
behaviour.