基于拓扑优化的小型飞机襟翼支架的轻量化设计

Lightweight design of small aircraft flap bracket based on topology optimization

飞机襟翼是与飞机机翼相连的运动机构,襟翼支架是襟翼的关键零件之一。针对襟翼支架轻量化问题,利用Altair Inspire软件对襟翼支架进行拓扑优化。优化后,襟翼支架质量由0.59 kg降至0.16 kg,减少0.43 kg,质量减少率为72.88%,安全系数为9.6,最大等效应力为22.01 MPa,远小于材料的屈服强度215 MPa,符合零件的使用需求。

The flap of an aircraft is a motion mechanism connected to the wing of the aircraft,and the flap bracket is the key mechanism of the flap.This article utilizes Altair Inspire software to optimize the topology of the flap bracket.The weight of the optimized support parts is reduced from 0.59 kg to 0.16 kg,with a weight reduction of 0.43 kg and a weight reduction rate of 72.88%.The factor of safety of the optimized support is 9.6,and the maximum equivalent stress is 22.01 MPa,which is far less than the yield strength of the material 215 MPa,meeting the use requirements of the parts.