Optimization and Comparison of Stiffened Panels with Sandwich Structures for Fuselages

摘要

Composite sandwich fuselages have a great application potential for the future aircraftsbecause of its desirable structural efficiency and functional integration advantage. In this paper,the fuselage is assumed to be a cylinder according to the geometry and load cases of A320.First, optimization for the composite stiffened and sandwich cylinders are respectively conducted.The optimum dimensions for both structures are determined using a weight-objectiveoptimization. The constraints imposed are based on the global stability and the material strength.The design parameters include the skin and core thicknesses, the stringer and frame sizes andthe composite layup. Secondly, the optimized stiffened and sandwich structures are comparedwith each other in terms of the weight and the sound insulation. It is found that the optimumstiffened cylinder is slightly lighter than the sandwich one, while its sound insulation is poorerthan the sandwich structure. In addition, the frames have a strong influence on the structuralstability of both stiffened and sandwich structures.