Abstract: A numerical analysis model for the bird-impact response of aircraft windshields was proposed by combining the dynamic explicit finite element code PAM-CRASH and the smoothed particle hydrodynamics (SPH) method. The dynamic response of an aircraft windshield to bird-impact loading was simulated by the proposed analysis model. The displacement-time curves for the four points on the medial axis of the aircraft windshield were calculated, the failure criterion for the aircraft windshield subjected to bird-impact loading was developed, and the failure state of the aircraft windshield under the given experimental conditions was numerically calculated. Numerical simulation results of the bird-impact process indicate that the SPH bird model can correctly model the breaking-up of the bird into debris particles. The good agreement between numerical and experimental results illuminates that the numerical simulation model developed in the present paper is valid.