Canard position and dihedral for boom reduction and pitch/directional control
US7416155B2 · kind B2 · utility
5Cited by
1References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 7, 2005 |
| Grant date | Aug 26, 2008 |
| Priority date | — |
| Expiry date | Jan 27, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/30
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A supersonic aircraft comprises a fuselage extending forward and aft, wings coupled to lateral sides of the fuselage, and canards coupled to lateral sides of the fuselage forward of the wings. The individual canards are configured to generate shocks that wrap around the fuselage and intersect with wing leading edges on opposing sides of the fuselage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.