Fitting for pivotally connecting aerodynamic control element to aircraft structure
US8286911B2 · kind B2 · utility
2Cited by
7References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 13, 2009 |
| Grant date | Oct 16, 2012 |
| Priority date | — |
| Expiry date | Oct 19, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method of installing an aerodynamic control element on an aircraft structure. The method comprising: attaching a fitting to the aircraft structure, the fitting comprising a pair of hinge ribs extending away from the aircraft structure and a spacer extending between the pair of hinge ribs; maintaining a desired distance between the pair of hinge ribs with the spacer as the fitting is attached; and pivotally mounting the aerodynamic control element to each hinge rib via a respective hinge.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.