Removable or hinged component for covering openings in the fuselage of an aircraft
US5084120A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 4, 1989 |
| Grant date | Jan 28, 1992 |
| Priority date | — |
| Expiry date | Dec 4, 2009 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/24777
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A component for cladding apertures in the fuselage of an aircraft is to be of lighter weight and more corrosion resistant as compared with known claddings. The component is manufactured of carbon fibre reinforced curable synthetic resin and comprises a base layer (2) onto which U-profiles (4, 4') and L-profiles (5, 5') are placed in spaced apart interrelationship, which during the manufacture are held in place by a grid (14) comprising angular bridge members. A vacuum foil 7 is applied over this assembly and is adhesively bonded along the edges of the base layer (2') to the supporting surface (1). The space between the vacuum foil (7) and the supporting surface (1) is evacuated and curing proceeds at an elevated temperature and pressure. After complete curing the vacuum foils (7) and the grid (14) are removed.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.