Method for assembling window coaming on a fuselage, coaming to be used, and aircraft fuselage provided with such coaming
US8940215B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Apr 22, 2011 |
| Grant date | Jan 27, 2015 |
| Priority date | — |
| Expiry date | Aug 19, 2031 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/24074
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A reduction of the multiple costs of manufacture, assembly use, and upkeep connected with the assembly of window frames on aircraft fuselages. To this end, the invention provides a particular shape for the frames connected to the fuselage skin according to a specific assembly method. The shape enables, among other things, the window frames to be fitted onto the skin by means of adhesion and also frames to be dispensed with between the fuselage and the window. In one embodiment, composite material window frame has a wall totally in the shape of a crown that is connected, through co-adhesion, to the inner surface of the fuselage skin, also made of composite material. The skin is cut into a window-receiving opening, and the frame has a T-shaped cross section, wherein the bar of the “T” that forms the crown includes two portions having substantially equal lengths “T.”
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.