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将飞机结构设计的尽可能理想,如重量轻、强度高、耐久性好等,一直是飞机结构设计师的愿望。应用子模型分析技术,从全局模型中提取感兴趣部位进行细节分析,然后加入损伤容限约束条件,对结构细节进行多目标优化设计。讨论了机身开口结构几何参数对结构寿命的影响,结果显示加强结构附近剩余强度可能发生不减反增的现象,裂纹扩展寿命对开口倒角半径并不很敏感,增加带板厚度在一定范围内能够提高结构寿命。该文方法具有较好的精度和准确性,同时为开口结构设计、优化和检修提供参考及指导。
It is always the desire of aircraft structural designers to make the aircraft structure design as ideal as possible, such as light weight, high strength and durability. Applying the sub-model analysis technique, we extract the region of interest from the global model for detailed analysis, and then add the constraint conditions of damage tolerance to optimize the structural details by multi-objective optimization. The influence of geometric parameters of the structure of the fuselage on the structure life is discussed. The results show that the residual strength near the reinforced structure may not decrease but increase inversely. The crack propagation life is not sensitive to the radius of the chamfered opening. The thickness of the strip is increased within a certain range Within can improve the structure of life. This method has better accuracy and accuracy, and provides reference and guidance for the design, optimization and maintenance of the open structure.