Research On New Method Of Composite Wing Structural Configuration Selection

With the widely use of composite materials, the development of computer technology andhigh-performance design requirements, wing configurations have become more and morecomplex.New type of wing configuration has appeared, such as composite structures, sandwichstructures, integral structure, smart structure and so on. Wing configuration design focus on not onlythe strength and stiffness, but also pay more attention to safe life and damage tolerance properties ofthe structure.Therefore, the wing structure design has become increasingly difficult.There is nouniversal method for configuration selection currently. So it still largely relies on past experience basedon the prototype aircraft.In order to partially replace experience in wing structure configuration selection and reducereliance of FEM on the preliminary design, this paper proposes a quantitative method of wing structureconfiguration selection. With the configuration stress-passing characteristic analysis and finite elementanalysis, the quantitative models select the wing geometry parameters and load parameters to establisha mathematical model according to strength, stiffness and stability requirements. Then mathematicalmodels can be used to estimate the weight and structural efficiency of the wing structure. This paperalso gives the the experience curves which expresses the support stiffness of the stringers.The rapiddesign can be achieved by the experience curve. Finally, the quantitative method is applied to twospecific wing structure designs which can prove its reliability and generality.