Abstract
The paper studies the bird strike against composite material tail leading edge under Chinese HB7084-94 condition, including material failure process, by using explicit finite element method. SPH grid free method is taken to describe birds splashing during the strike. The calculation results show that, the original design composite structure could not meet the requirements of standard HB7084-94 towards the aircraft vertical tail anti-bird impact performance. The optimized design increases the ply number of the leading edge from 6 to 22. With a weight cost of 2.957Kg, the optimized design could meet the standard.
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