Numerical analysis and experimental verification of bird impact on civil aircraft's horizontal tail wing leading edge

Tensile tests of 2024-T3 and 7075-T6 aluminum alloy under different strain rates were conducted on an electronic hydraulic testing machine and split Hopkinson tensile bar (SHTB) system. A Johnson-Cook model which can reflect the strain rate hardening effect of the aluminum alloys were fitted. The limit tensile loads and shear loads of 7 kinds of rivets were obtained by SHTB dynamic tensile tests. By coupling the smooth particle hydrodynamics (SPH) method and finite element method, and using the constitutive equation of aluminum alloys and dynamic failure parameters, a numerical model of bird impact on civil aircraft's horizontal tail wing leading edge was established by utilizing the transient dynamic software PAM-CRASH. The bird impact test was performed to validate the numerical calculation results. The calculation results are consistent with the experimental results, which shows that the numerical calculation model is reasonable and reliable. The building-block experimental and analysis process provide reference to the anti-bird impact design of civil aircraft structure.