Method and device for yaw controlling of an aircraft
US8584990B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Feb 9, 2012 |
| Grant date | Nov 19, 2013 |
| Priority date | — |
| Expiry date | Feb 9, 2032 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0066
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
According to the invention, an alert may be generated when a sudden inversion of the rudder occurs. To this end, the pilot having beforehand moved a commanding system in such a manner that the movement of the commanding system overcomes the position of the commanding system corresponding to the maximum rotation breakpoint in one of the rotating directions of the rudder. The alert is launched if, during a first time interval having a predetermined duration, the pilot moves the commanding system in such a manner that the movement of the commanding system overcomes the position of the commanding system corresponding to the maximum rotation breakpoint in the other rotating direction of the rudder, thereby indicating a sudden rudder inversion and a potential unsafe condition to be corrected by the pilot.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.