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针对某型航空轮毂在径向-侧向联合载荷试验中的辐板断裂事故,建立了轮毂的力学模型,利用ANSYS软件进行有限元分析,获得了等效应力图,并进行了试验研究。结果表明,最大应力出现在辐板与毂部的过渡圆弧处;原型轮毂的最大等效应力大大超过了材料的许用应力是导致辐板失效的根本原因;优化轮毂的最大应力小于材料的许用应力,试验通过;有限元分析结果与试验结论吻合。
Aiming at the failure of a certain type of aviation hub in the radial-lateral joint load test, the mechanical model of the hub was established, and the finite element analysis was carried out by ANSYS software. The equivalent stress diagram was obtained and tested. The results show that the maximum stress occurs at the transition arc between the web and the hub. The maximum equivalent stress of the prototype hub exceeds the allowable stress of the material, which is the root cause of failure of the web. The maximum stress of the optimized hub is less than that of the material Allowable stress, the test passed; Finite element analysis and experimental conclusion.