A Research On Optimization Method Of Composite Central-Wing

As an excellent material,the composite material has a lot of advantages,for example,high specificstrength and high specific stiffness,so it has been widely used in aircraft structures. In order to carryout composite structural design, the first step should be choosing the configuration.Selecting theappropriate configuration is an important way to reduce the weight of composite structures.The object of study in this paper is the central wing structure.Firstly, the article makes stressanalysis for three configurations of the central wing structure(beam layout, distribute flange layoutand multi-cell layout),and the failure modes are developed respectively.Then,the paper studies theweight characteristics of composite central wing structures, and draws the diagrams of load and massdensity. After obtaining the load, we can select the optimal configuration according to thediagram.Secondly,the paper makes further analysis to identify larger influence factors of the diagrams.In the case of changing structure height without changing material, the optimal configuration of thestructure may need to be adjusted. For a given structure, changing it’s material (or changing theallowable values of the material), generally leads to modify the configuration.Finally, the method isapplied to the design of the wing structure. The paper has established a finite element model of thewing and carried out structural optimization design.Significantly reducing the weight of the wingstructure with the method, the paper has successfully completed the design task.