SAMPE EUROPE 32 nd International Conference – SEICO 11 Paris pages:1-1
SAMPE EUROPE 32 nd International Conference – SEICO 11 location:Paris date:March 28 - 29, 2011
Composite sandwich fuselages have a great application potential for the future aircrafts
because 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-objective
optimization. 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 and
the composite layup. Secondly, the optimized stiffened and sandwich structures are compared
with each other in terms of the weight and the sound insulation. It is found that the optimum
stiffened cylinder is slightly lighter than the sandwich one, while its sound insulation is poorer
than the sandwich structure. In addition, the frames have a strong influence on the structural
stability of both stiffened and sandwich structures.