A Research On Structure Design Of Composite Fuselage Panel

The application proportion of composites has become an important advanced standard formodern airliners. To apply composite materials in these structures could reduce weight significantly,and improve flight performances. Therefore the research on structure design of the composite fuselagestructures is a matter of great significance in engineering. This research work mainly includes thefollowing several aspects：A type of simplified model was proposed to calculate the critical buckling load of curved plate.When the local buckling occurs, stringers and frames contribute a torsional constraint to the boundaryof curved plate. The beam elements given only torsional stiffness were built in the periphery of theplate to simulate this boundary conditions. Two type of model, simplified model and high precisionmodel, were built to carry out buckling analysis. From the analysis results of the two kinds of modelwe can see that the simplified model has very high creditability.The buckling and post-buckling response of compressed stiffened plate is analyzed in this paper.To the structure of thin-walled and stiffened cylindrical shell, because of the stringers, stiffened platedo not lose the load-carrying capability after reaching the skin critical load. Because the bendingstiffness of stringer is very large, the post-buckling critical load of this structure is much higher thanthe skin buckling load. The stress would be redistributed from skin to stringer when the skin bucklingoccurs. The conception of effective skin was defined to calculate the skin post-buckling load capacity,and the post-buckling critical load was estimated by the Euler buckling model.Finally, it took a setted shape parameters of stiffened shell structure of fuselage for example. Thispaper used sequential quadratic programming method to obtain the optimum solution of minimumstructure weight which is based on simplified model of skin local buckling.