Self-stiffened skin for aircraft fuselage including stringers with a closed section and associated manufacturing method

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United States of America Patent

PATENT NO 9446834
SERIAL NO

14140513

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems.

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Patent Owner(s)

  • AIRBUS OPERATIONS SAS

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Delahaye, Romain Colomiers, FR 28 199
Lieven, Patrick Fronton, FR 32 140

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