Design, Analysis, and Testing of Integrally Stiffened Composite Centre FuselageSkin for Future Fighter Aircraft

摘要

A center fuselage skin made of one piece carbon fiber composite monocoque withdouble curvature, stiffened with simultaneous curved frames and longerons, is described. The basic design, material selection and stressing of typical features are discussed and compared with test results. The design is assessed in terms of weight reduction and production cost considerations.