Power supply system and method on board an aircraft

• US 7,737,577 B2
• Filed: 10/23/2007
• Issued: 06/15/2010
• Est. Priority Date: 10/25/2006
• Status: Expired due to Fees

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: Alejo, Dominique, Prisse, Lucien, Langlois, Olivier, Foch, Etienne
• Primary Examiner(s): RUTLAND WALLIS, MICHAEL
• Application Number:
  US11/877,278
• Publication Number:
  US 20080100136A1
• Time in Patent Office: 966 Days
• Field of Search: 307/45, 307/19, 307/9.1, 307/18, 700/36
• US Class Current: 307/19
• 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

A system and a power supply method, on board an aircraft, in which the power supply system of an aircraft includes several generators powering with 230 volts A.C. several distinct electrical cores, wherein the various loads of the aircraft are connected to each of these cores. Each core includes an input driver, several identical power modules, means of placing in parallel several power modules including interconnection inductances between power modules, and a switching matrix including a set of relays, means of piloting the relays of the switching matrix, so as to reconfigure all of these relays in the case of failure of a power module, several output filters, and relays of the switching matrix that may each be connected to at one load.

Claims

1. A power supply system of an aircraft, comprising:

several generators powering with 230 volts A.C. several distinct electrical cores, wherein various loads of the aircraft are connected to each of these electrical cores, in which each electrical core includes;

an input driver,

several identical power modules, each power module of the several identical power modules includes a network connection permitting connection to a controller and a synchronization line permitting connection to the other power modules,

means for placing in parallel the several power modules including interconnection inductances between the power modules, and a switching matrix including a set of relays,

means for controlling the relays of the switching matrix, so as to reconfigure all of these relays in an event of failure of a power module, thus working power modules can provide power that the failed power module can no longer provide,

several output filters, and

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

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

3. The system according to claim 2, further comprising grouped command electronics associated to each power module.

4. The system according to claim 2, further comprising a controller that manages the different configurations according to the state of the system and the requests.

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

6. The system according to claim 1, in which the power modules are standard modules.

7. The system according to claim 1, in which several power modules are positioned in parallel.

8. The system according to claim 5, in which the AC/DC converter is a diode rectifier.

9. The system according to claim 5, in which the AC/DC converter includes one or several power modules paired in parallel.

10. A method for implementing the system according to claim 1, in which several power modules are placed in parallel.

11. The method according to claim 10, in which several functions are carried out with each of the power modules.

12. An aircraft including the system of claim 1.

13. A power supply system of an aircraft, comprising:

several generators powering with 230 volts A.C. several distinct electrical cores, wherein various loads of the aircraft are connected to each of these electrical cores, in which each core includes;

an input driver,

several identical power modules,

means for placing in parallel the several power modules including interconnection inductances between the power modules, and a switching matrix including a set of relays,

means for controlling the relays of the switching matrix, so as to reconfigure all of these relays in an event of failure of a power module,

several output filters, and

relays of the switching matrix that may be connected to at least one load; and

each power module of the several identical power modules includes;

a power supply which inputs +/−

270 volts D.C.,

a network connection, permitting a connection to a controller,

synchronization line, permitting a connection to the other power modules,

power semiconductor components,

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

outputs to a load,

a control board, and

interconnection inductances.