Dynamic response of bird strike on aluminum honeycomb-based sandwich panels

Numerical simulation is often used in the design of aircraft structural components subjected to bird-strike loads. To verify the numerical method, a test of bird striking was performed on honeycomb-based sandwich panels made from 3003 aluminum honeycomb and 2024-T3 aluminum skin. The dynamic responses of displacement and strain on the rear skin of the sandwich panel during bird striking were measured using strain gauges and a laser sensor, respectively. A numerical model of bird striking was developed with a nonlinear, finite-element program. A coupling smooth particle hydrodynamics-finite-element analysis algorithm was used to simulate the interaction of the impacting contact between the bird and the target. The numerical simulation results were compared with the tests, and they are in good agreement, which validated the reasonableness of the numerical model established in the present paper. This shows the potential of using the FEM in simulating the dynamic response of aircraft structural components in bird-strike events.