Section of aircraft fuselage in composite material with a constant internal profile
View Patent ↗The disclosed embodiments concern an aircraft fuselage section made of composite material with an internal skeleton having frames that form the radial structure of the fuselage and stringers that form the longitudinal structure of said fuselage, and a skin made of composite material, surrounding the internal skeleton, with said skin having an evolving thickness along a longitudinal axis X, with an approximately constant, regular interior profile. The disclosed embodiments also concern a process for manufacturing the skin of an aircraft fuselage section made of composite material, having a draping operation for strips of fibers precoated with resin around a mold, with the number of strips of fibers varying longitudinally depending on the area of the fuselage being considered so as to create a skin with an evolving thickness.
1. 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.
2. The aircraft fuselage section in claim 1 , wherein the variation in skin thickness is obtained by superimposing and interlacing strips of fibers, with the number of strips varying as a function of the desired thickness.
3. The aircraft fuselage section in claim 1 , wherein the frames are F-shaped frames with built-in attachment clips.
4. The aircraft fuselage section in claim 1 , wherein the stringers are constant in height.
5. The aircraft fuselage section in claim 1 , wherein the frames are constant in height.
6. An aircraft comprising at least one fuselage section made of composite material according to claim 1 .
7. The aircraft fuselage section in claim 1 , wherein the internal profile is constant along the longitudinal axis of the fuselage section for the entire longitudinal length of the fuselage section between the longitudinal joining areas and excluding any opening areas in the fuselage section.
8. The aircraft fuselage section in claim 7 , wherein the opening areas are selected from a group consisting of hatches, doors and inspection ports.