FADEC AND AVIONIC COMPONENT DISTRIBUTED ARCHITECTURE

• US 20100292870A1
• Filed: 08/20/2008
• Published: 11/18/2010
• Est. Priority Date: 09/03/2007
• Status: Active Grant

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Durand, Nathalie, Leborgne, Frederic, Saint Marc, Laurent, Brunel, Luc, Immordino, Thierry, Alexandre, Matthieu, Feau, Julien, Belkadi, Jean-Francois, Zaccaria, Patrick
• Granted Patent: US 8,825,227 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64D 31/00 Power plant control systems; Arrangement of power plant control systems in aircraft
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C

Abstract

The invention relates to a device for motorized aircraft comprising at least one avionic component (300) positioned in the said aircraft, at least one engine interface (310) positioned in the said aircraft and at least one engine controller (315) positioned in or near an engine (320) of the said aircraft. According to the device of the invention, the said at least one engine interface (310) is designed to exchange data between the said at least one avionic component (300) and the said at least one engine controller (315). The said at least one engine interface (310) is generic and able to communicate with engine controllers (315) of various types that may be mounted on said aircraft. The said at least one engine controller is specific to a particular engine.

Claims

1. Device for an engine-operated aircraft comprising at least one avionic component positioned in the said aircraft and at least one engine control positioned in or close to an engine of the said aircraft, this device being characterized in that it further comprises at least one engine interface positioned in the said aircraft, the said at least one engine interface being adapted for exchanging data between the said at least one avionic component and the said at least one engine control, the said at least one engine interface being generic and adapted for communicating with engine controls of different types that can be mounted on the said aircraft, the said at least one engine control being specific to one type of engine.

2. Device according to the preceding claim, characterized in that the said at least one engine interface comprises means for selecting the said data exchanged between the said at least one avionic component and the said at least one engine control.

3. Device according to the preceding claim, characterized in that the said at least one engine interface comprises means for validating at least some of the said data exchanged between the said at least one avionic component and the said at least one engine control.

4. Device according to any one of the preceding claims, characterized in that the said at least one engine interface is at least partially implemented in a computer of LRU type.

5. Device according to any one of the preceding claims, characterized in that the said at least one engine interface is at least partially implemented in a modular avionic computer of IMA type.

6. Device according to any one of the preceding claims, characterized in that the said at least one engine interface comprises at least two redundant channels.

7. Device according to any one of the preceding claims, characterized in that the said at least one engine control comprises at least two redundant channels.

8. Device according to any one of the preceding claims, characterized in that the said aircraft comprises at least two engines, at least one engine interface and at least one engine control being associated respectively with each of the said at least two engines, and in that it further comprises means for segregation of the data exchanged in each of the systems made up of at least one engine interface and at least one engine control associated with each of the said at least two engines.

9. Device according to any one of the preceding claims, characterized in that it further comprises means for direct connection between at least one control element of the said aircraft and at least one engine control.