Flight control system for an aircraft
US8430354B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 6, 2010 |
| Grant date | Apr 30, 2013 |
| Priority date | — |
| Expiry date | Nov 1, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/50
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Power takeoff means (46, 47, 60, 61) for this flight control system adjacent to the aircraft engines (41, 42) are all-electric and this makes it possible to reduce the length of hydraulic connections leading to actuators of the controlled devices (54, 55, 66). Electrical generators are of different types to minimize the risk of a generic failure. Characteristically of the invention, some generators (60, 61) have a constant voltage to frequency ratio and directly or almost directly control electro-hydraulic pumps (64, 65), without modifying the current characteristic and with no power electronics. Furthermore, system reconfigurations are made possible by additional electrical connections (69, 70, 71, 72) in case of failure.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.