Research On The Buckling Design Method Of Stiffened Composite Wing Box Based On Structural Efficiency

The wing box is the main load—bearing structure, generally has very small surface curvature,which could be simplified to an equivalent box structure model. Compared with the composite stiffenedplate model, the composite box structure reflects the force bearing characteristics and the stresscharacteristics more accurately and expresses the relationship between wing spar, skin and stringermore clearly. This paper mainly uses the composite box structure as the research foundation, andanalysis the stress characteristics and load transferring characteristics of composite box, aiming torefine the design of composite wing structure.A rapid design method based on efficiency is proposed in this thesis for the wing panel structure.Firstly, as far as possible to abstract the composite wing structure and restore the real stress condition ofthe wing, a buckling model of reinforced box is abstracted, according to criterion of similar structure,load and material with the wing. Secondly, the experience curves which express the supportingstiffnessof the stringers and Farrar’s efficiency are drawn. Finally, in order to further summarize a bucklingdesign of composite stiffened box and achieve the layout and size optimization of composite stiffenedplate, the experience curve is applied to a central wing structure design, thus testing and verifying thedesign method.Combined with the empirical method and surrogate model method, the design method which ismainly applied to the wing structure, has the advantages of higher efficiency, smaller model andstronger versatility.