Lightweight design of aircraft flap mount based on Altair inspire

Abstract With the continuous improvement of aircraft energy efficiency requirements in the aviation industry, the lightweighting of aircraft flap structures has become an important way to improve fuel economy and maneuverability. Based on Altair Inspire software, this study takes the bracket of aircraft flap as the research object, constructs a multi-objective optimization model, and lightweight the design of the bracket of aircraft flap with the constraints of minimum safety factor, maximum deformation, and Mises stress distribution. The results show that after topology optimization, the mass of the bracket is reduced by 98%, and the material utilization rate of the flap bracket structure is improved, which provides a new method for the design of aviation components.