Splice joints for composite aircraft fuselages and other structures
US7325771B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 23, 2004 |
| Grant date | Feb 5, 2008 |
| Priority date | — |
| Expiry date | Jan 3, 2025 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/24661
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.