Bird strike simulation on sandwich composite structure of aircraft radome

A methodology for the numerical simulation of bird strike on a nose radome structure of an aircraft is presented. The simulation technique is based on a non-linear dynamic finite element analysis and is performed in two steps. The first step deals with the choice of suitable material models capable of representing the behaviors of the material systems used in the impact process. The second step deals with the numerical simulation of bird strike on aircraft radome structure. The influence on the numerical results of the critical modeling issues such as the mesh density, the substitute bird flexibility and contact interfaces parameters are discussed briefly, and the of strain rate effect of material is presented by comparing the calculations. Then, the analytical method is employed to predict the amount of energy absorbed by the radome structure. As the impact location varys, the tendency of the energy absorbed by the structure is given.