Electrical conversion and distribution system for an aircraft

Patent metadata

Field	Value
Publication number	US-2016352129-A1
Application number	US-201515113872-A
Country	US
Kind code	A1
Filing date	Jan 28, 2015
Priority date	Jan 31, 2014
Publication date	Dec 1, 2016
Grant date	—

Abstract

The invention relates to an electrical conversion and distribution system for an aircraft, the system comprising at least one synchronous starter-generator (S/G 1, S/G 2 ) intended to be coupled to an engine (Engine 1 ) of the aircraft, at least one conversion path comprising a plurality of power converters (CVn, CV′n) associated with switching means suitable for supplying at least one charge (CAC 1, CAC 2, CAC 3, CAC 4, P 1, P 2 ) from at least one source (S/G 1, S/G 2, AUX S/G 1, AUX S/G 2, GPU 1, GPU 2 ), and at least one distribution path suitable for supplying electrical charges (CT 1 n , SW 1 n , CT 2 n , SW 2 n ).

First claim

1 . An electrical conversion and distribution system for an aircraft, with the system comprising:
at least one synchronous generator-starter intended to be coupled to an engine of the aircraft, at least one conversion path comprising at least a first direct voltage bus connected to a plurality of power converters suitable for converting a direct voltage into an alternating voltage or conversely, at least one line intended to be connected to a charge requiring an alternating voltage and at least another line intended to be connected to an alternating voltage source, with the conversion path further comprising first switching means suitable for selectively connecting or disconnecting each power converter to/from the first direct voltage bus, and second switching means suitable for selectively connecting or disconnecting each of said lines to/from each converter, at least one distribution path comprising at least one second direct voltage bus suitable for supplying at least one electrical charge, with the synchronous generator-starter being connected to the first and/or second direct voltage bus through at least one line equipped with a voltage rectifier.

2 . A system according to claim 1 , further comprising a first generator-starter and a second generator-starter intended to be coupled to the same engine of the aircraft, with the first generator-starter being connected to the first direct voltage bus through a line equipped with a first voltage rectifier, with said second generator-starter being connected to the second direct voltage bus through another line equipped with a second voltage rectifier.

3 . A system according to claim 1 , wherein the first and second direct voltage buses are suitable for being selectively connected together through switching means.

4 . A system according to claim 1 , wherein the first direct voltage bus and/or the second direct voltage bus is/are connected to at least one battery through a line equipped with a Boost converter.

5 . A system according to claim 1 , wherein at least one battery is connected to the generator-starter through a line equipped with a transformer-rectifier.

6 . A system according to claim 1 , wherein the conversion path comprises at least one line connecting an alternating voltage bus intended for a home network of the aircraft, to a switching matrix.

7 . A system according to claim 6 , wherein the line connecting the switching matrix to the alternating voltage bus intended for the home network is provided with a sine filter.

8 . A system according to claim 1 , further comprising at least one auxiliary synchronous generator-starter intended to be coupled to an auxiliary power unit and connected through a line to the first direct voltage bus and/or the second direct voltage bus.

9 . A system according to claim 1 , further comprising:
at least a first and a second synchronous generators-starters intended to be coupled to the same engine of the aircraft, at least a first and a second conversion paths, each comprising at least a first direct voltage bus connected to a plurality of power converters suitable for converting a direct voltage into an alternating voltage or conversely, at least one line intended to be connected to a charge and at least one other line intended to be connected to an alternating voltage source, with each conversion path further comprising first switching means suitable for selectively connecting or disconnecting each converter to/from the first direct voltage bus, and second switching means suitable for selectively connecting or disconnecting at least one of said lines to/from one of the converters, at least a first and a second distribution paths, each comprising at least a second direct voltage bus suitable for supplying electrical charges, with the first synchronous generator-starter being connected to the first and/or second direct voltage bus of the first conversion path or the first distribution path through at least a line equipped with a voltage rectifier, with the second synchronous generator-starter being connected to the first and/or second direct voltage bus of the second conversion path or the second distribution path, through at least one line equipped with a voltage rectifier.

10 . An aircraft, comprises comprising at least one system according to claim 1 .

Assignees

• Safran Electrical & Power

Inventors

• Casimir Roland
• Hadjidj Djemouaï
• Giorgis Vincent

Classifications

• H02J7/143

  with multiple generators · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H02J7/1423

  with multiple batteries · CPC title

• F02N11/08

  Circuits specially adapted for starting of engines · CPC title

• H02J2105/32

  for aircrafts · CPC title