Method and arrangement for fastening composite aircraft skins
US5845872A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jun 2, 1995 |
| Grant date | Dec 8, 1998 |
| Priority date | — |
| Expiry date | Jun 2, 2015 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D45/02
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The present invention provides a method of fastening an outer composite aircraft skin (12) to an inner substructure (14), which may be the wall of a fuel tank. The method includes the steps of incorporating an electrically conductive layer (26) in an outer surface of the outer composite skin (12), inserting a bolt (11) through the electrically conductive layer (26) and the outer composite skin (12) and through the inner substructure (14), securing the bolt (11) by means of a nut (22) directly or indirectly engaging the inner surface of the inner substructure (14), and applying insulating material (34) over the head (16) of the bolt.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.