Control configured vortex flaps
US5094411A · kind A · utility
40Cited by
16References
11Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Oct 19, 1990 |
| Grant date | Mar 10, 1992 |
| Priority date | — |
| Expiry date | Oct 19, 2010 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/10
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Individually deflectable, segmented, vortex flaps are provided on the leading edges of a delta wing supersonic aircraft to permit selective lateral and directional control moments to be created on the aircraft at high angles of attack, where conventional elevons and rudders have become ineffective. By selectively deflecting the segmented vortex flaps simultaneously in the same direction or differentially, the lateral and directional control of high-swept, thin wing, supersonic speed aircraft, at high angles of attack, is improved.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.