The present study concern birdstrike on aeronautic structures. We consider both on one hand a mathematical approach followed by a numerical study and the other hand an experimental study allowing to validate the results obtain by the numerical way. From the theoretical point of view, we consider in the mathematical model of the structure large deformation, specific materials described by nonlinear law and the nonlinear behavior describing the contact between the structure and the projectile. The numerical simulation is performed by coupling the finite element method with the Smooth Particle Hydrodynamic method (SPH). Lastly in order to obtain short elapsed time of simulation the computational code is paralyzed and vectorized. The results of simulation are compared successfully with experimental study performed in laboratory.