航空轮胎有限元分析

Finite Element Analysis on Aircraft Tire

以H44.5×16.5-21航空轮胎为例,基于Abaqus有限元分析软件对轮胎的静态力学性能进行仿真分析。结果表明:随着下沉量增大,轮胎接地最大应力逐渐由胎面中心向胎肩部位转移,胎肩比胎冠磨损更严重;充气压力不足时,轮胎下沉量增大,滚动阻力提高,同时轮胎发生翘曲,胎肩部位应力集中更明显。

Taking H44.5 × 16.5- 21 aircraft tire as an example, the static mechanical property of tire was simulated and analyzed with finite element analysis software Abaqus. The results showed that, with the increase of deflection, the maximum contact stress of the tire gradually moved from tread center to shoulder which caused more severe wear of shoulder than crown. When the inflation pressure was insufficient, the deflection enlarged, and the rolling resistance increased, and the tire warped which resulted in more significant stress concentration in the shoulder region.