Patent ID: 8876049

Claim:
An aircraft fuselage section having a longitudinal joining area at each end of the section for joining the fuselage section to another fuselage section and made of composite material comprising: an internal skeleton with a plurality of frames forming a radial structure of the fuselage section and stringers forming a longitudinal structure of said fuselage section, and a skin made of composite material surrounding the internal skeleton, the skin having an internal and an external profile, with the internal skeleton abuttingly engaging the internal profile of the skin and said skin having a variable thickness as measured between the internal and external profiles, the fuselage section having a longitudinal length extending along a longitudinal axis of the fuselage section between the longitudinal joining areas, the external profile having a constant linear change along the longitudinal length of the fuselage section between the longitudinal joining areas, and the internal profile being constant along the longitudinal axis of the fuselage section for the longitudinal length of the fuselage section between the longitudinal joining areas, wherein the internal and external profiles define a conical exterior shape of the skin.