Self-stiffened skin for aircraft fuselage including stringers with a closed section and associated manufacturing method
US9446834B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 25, 2013 |
| Grant date | Sep 20, 2016 |
| Priority date | — |
| Expiry date | Nov 12, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/13
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.