Lightweight design of small aircraft flap bracket based on topology optimization
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.
万方数据
维普
