POWER SUPPLY SYSTEM AND METHOD ON BOARD AN AIRCRAFT

• US 20080100136A1
• Filed: 10/23/2007
• Published: 05/01/2008
• Est. Priority Date: 10/25/2006
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: LANGLOIS, Olivier, Prisse, Lucien, Foch, Etienne, Alejo, Dominique
• Granted Patent: US 7,737,577 B2
• Time in Patent Office: Days
• US Class Current: 307/9.1
• CPC Class Codes: H02J 1/10 Parallel operation of dc sources
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 3/38 Arrangements for parallely feeding a single network by two or more generators, converters or transformers
• CPC Class Codes: H02J 4/00 Circuit arrangements for mains or distribution networks not specified as ac or dc
• CPC Class Codes: H02J 5/00 Circuit arrangements for transfer of electric power between ac networks and dc networks H02J3/36 takes precedence

Abstract

The invention relates to a system and a power supply method, on board an aircraft. The power supply system of an aircraft comprises several generators powering with 230 volts A.C. several distinct electrical cores, wherein the various loads of the aeroplane are connected to each of these cores, in which each core comprises:

• • an input driver (40),
  • several identical power modules (CVS1 . . . CVSn),
  • means of placing in parallel several power modules comprising interconnection inductances (41) between power modules, and a switching matrix (42, 44) comprising a set of contactors,
  • means (52) of piloting the contactors of the switching matrix (42, 44), so as to reconfigure all of these contactors in the case of failure of a power module,
  • several output filters (43),
  • contactors (44) of the switching matrix (42, 44) that may each be connected to at one load (Cij).

Claims

1. Power supply system of an aircraft comprising several generators powering with 230 volts A.C. several distinct electrical cores, wherein the various loads of the aeroplane are connected to each of these cores, in which each core comprises:

an input driver,

several identical power modules,

means for placing in parallel several power modules comprising interconnection inductances between power modules, and a switching matrix comprising a set of contactors,

means for piloting the contactors of the switching matrix, so as to reconfigure all of these contactors in the event of failure of a power module,

several output filters,

contactors of the switching matrix that may be connected to at least one load.

2. System according to claim 1, comprising preload systems permitting the power components to be powered and protected.

3. System according to claim 2, comprising grouped command electronics associated to each power module.

4. System according to claim 2, comprising a supervisor that manages the different configurations according to the state of the system and the requests.

5. System according to claim 1, in which the input driver comprises an AC/DC converter and isolating contactors equipped with a preload system.

6. System according to claim 1, in which a power module comprises:

power supply inputs +/−

270 volts D.C.,

a network connection, permitting a connection to the supervisor,

a synchronisation line, permitting a connection to the other modules,

power semiconductor components,

igniters permitting the ignition and the extinction of the power components,

outputs to a load,

a control board,

interconnection inductances.

7. System according to claim 1, in which the power modules are standard modules.

8. System according to claim 1, in which several power modules are positioned in parallel.

9. System according to claim 5, in which the AC/DC converter is a diode rectifier.

10. System according to claim 5, in which the AC/DC converter comprises one or several power modules paired in parallel.

11. Method for implementing the system according to claim 1 in which at least one “

power module”

—

“

load”

unit is configured.

12. Method according to claim 11, in which several power modules are placed in parallel.

13. Method according to claim 11, in which several functions are carried out with each of the power modules.

14. Aircraft featuring a system of claim 1.