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

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Journal of Vibration and Shock ›› 2015, Vol. 34 ›› Issue (14) : 172-178.

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

XIE Can-jun1,2，TONG Ming-bo1，LIU Fu2，GUO Ya-zhou3，ZHU Shu-hua1

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Abstract

Tensile tests of 2024-T3 and 7075-T6 aluminum alloy under different strain rates were conducted by the electronic hydraulic testing machine and split Hopkinson tensile bar (SHTB) system. Johnson-Cook model which can reflect strain rate hardening effect. of the aluminum alloys were fitted. Limit tensile load and shear load of 7 kinds of rivet was obtained by SHTB dynamic tensile tests. By coupling Smooth Particle Hydrodynamics (SPH) method and finite element method, using the constitutive equation of aluminum alloys and dynamic failure parameters, the 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 result. The calculation result is consistent with the experimental result, which shows that the numerical calculation model is reasonable and reliable. The building-block experimental and analysis process provides reference for anti-bird impact design of civil aircraft structure.

Key words

bird impact / numerical analysis / constitutive model / horizontal tail wing / experiment

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XIE Can-jun1,2，TONG Ming-bo1，LIU Fu2，GUO Ya-zhou3，ZHU Shu-hua1. Numerical analysis and experimental verification of bird impact on civil aircraft’s horizontal tail wing leading edge[J]. Journal of Vibration and Shock, 2015, 34(14): 172-178

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