Aircraft structure including composite beam and composite panel with metal foil therebetween
US7874518B2 · kind B2 · utility
5Cited by
19References
12Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 16, 2006 |
| Grant date | Jan 25, 2011 |
| Priority date | — |
| Expiry date | Sep 21, 2028 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/26
- WIPO fieldOther special machines
- WIPO sectorMechanical engineering
Abstract
A method and article of manufacture of joining a stringer to a wing or tail panel and curing a wing or tail panel is disclosed. A sheet of titanium is placed between a cured stringer and an uncured wing or tail panel. The stringer, wing or tail panel and sheet are then placed within a vacuum bag, and gas is pumped out of the bag. The bag is then placed in an auto-clave to cure the wing or tail panel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.