STUDY OF FUSELAGE OPENING STRUCTURE BASED ON DAMAGE TOLERANCE OPTIMIZATION

It has been the desire of aircraft designers that the structures were devised as ideal as possible, such as lighter weight, higher strength and better durability. The sub-model analysis technology is applied to extract the region of interest from global model for detail analysis. Introducing the damage tolerance constraint conditions, muti-objective optimization for the detail design is completed. The relationships between structure life and geometrical parameters of fuselage opening are discussed. The results reveal that residual strength near the reinforcement structure may rise rather than decrease; crack life is not sensitive to fillet radius of opening; increasing the thickness of skin in a certain range can improve structure life. The solutions of proposed method have better accuracy, which provides reference and guidance for the designing, optimization and maintenance of opening structures.