Adhesive Strength Analysis And Optimization Design Of Key Composite Wing Structure

As advanced composite structures are widely used in the wing structures, thus manyresearchers pay more attention to the research on the joint analysis of composite wing structures. Alarge number of experiment research shows that the failure of connection is the reason of losingeffectiveness in wing structures for the most part. As the key structure of wing,the connection ofskin and support construction is glue joint. Thus strength analysis of the glue joint between skinand stringers, skin and beam edge has practical engineering significance. With the development ofFEM, there is no need to rely solely on the experiment research. Many researchers do jointstrength analyze based on the theory study and numerical simulation.By studying basic theories and methods which is already existed of adhesive strength, thispaper presents an analysis method of adhesive strength based on PATRAN/NASTRAN finiteelement software. This method combines the damage of adhesive layer and laminated plate.Interfacial layer based on cohesive model and use relative separation criterion to verdict the initialdamage. As for damage propagation, the secondary energy criterion is adopted. The initial damageof laminated plates is using Hashin failure criterion to determine. The degradation model ofnonlinear index mode is used to simulation the degradation of the material properties. Finiteelement model is set up to verify the feasibility and veracity of this method.Analysis of complex wing structures with the method above, which focuses on the adhesivelayer between skin and beam edge. On this basis, the influence of glue material, glue thickness,glue area to ultimate strength is studied. At the same time, this paper has do some discussion onthe influence of angle between layers, layer than, stacking-sequence to ultimate strength. In theend, complete the optimization design of wing structures with adhesive layer.