Load optimized redundant flight control surface actuation system and method
US8033509B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 27, 2007 |
| Grant date | Oct 11, 2011 |
| Priority date | — |
| Expiry date | May 21, 2029 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/40
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft flight surface control system and method simultaneously provides the benefits of both an active/active system architecture and in active/standby system architecture. The system is preferably implemented using hydraulic actuator assemblies and electromechanical actuator assemblies coupled to the same flight control surface. During normal system operations the electromechanical actuator assemblies are energized to supply a relatively minimal force to associated flight control surfaces. In effect, the electromechanical actuators, although energized, may be pulled along by the associated hydraulic actuator assemblies, until needed. Thus, the electromechanical actuator assemblies are controlled in a manner that closely resembles the active/standby architecture.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.