Aircraft power management system and method for managing power supply in an aircraft

Patent metadata

Field	Value
Publication number	US-9787092-B2
Application number	US-201414552593-A
Country	US
Kind code	B2
Filing date	Nov 25, 2014
Priority date	Nov 28, 2013
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

An aircraft power management system includes an electrical power supply input configured to be coupled to an electrical power supply, a first power supply bus bar coupled to the power supply input, at least one primary electrical equipment including a primary load coupled in parallel to the first power supply bus bar, a bus bar switch configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment, a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar, if the monitored power demand of the primary load exceeds a primary threshold, and at least one tertiary electrical equipment including a tertiary load coupled to the first power supply bus bar downstream of the at least one primary electrical equipment.

First claim

The invention claimed is:

1. A power management system, comprising:
an electrical power supply input configured to be coupled to an electrical power supply;
a first power supply bus bar coupled to the power supply input;
at least one primary electrical equipment including a primary load and a bus bar switch, the primary load being coupled to the first power supply bus bar, and the bus bar switch being configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment; and
at least one tertiary electrical equipment including a tertiary load being coupled to the first power supply bus bar downstream of the at least one primary electrical equipment parallel to the primary load,
wherein the at least one primary electrical equipment further includes a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar downstream of the at least one primary electrical equipment, when the monitored power demand of the primary load exceeds a primary threshold, the primary threshold being zero.

2. The power management system according to claim 1 , further comprising:
at least one secondary electrical equipment including a secondary load and a bus bar switch, the secondary load being coupled to the first power supply bus bar downstream of the primary electrical equipment and upstream of the tertiary electrical equipment parallel to the primary load, and the bus bar switch of the secondary electrical equipment being configured to selectively deactivate the first power supply bus bar downstream of the secondary electrical equipment.

3. The power management system according to claim 2 , wherein the at least one secondary electrical equipment further includes a load monitoring device configured to monitor the power demand of the secondary load and to output a deactivation signal to the bus bar switch of the secondary electrical equipment for selectively deactivating the first power supply bus bar downstream of the secondary electrical equipment, when the monitored power demand of the secondary load exceeds a secondary threshold.

4. The power management system according to claim 1 , further comprising:
a second power supply bus bar coupled to the power supply input in parallel to the first power supply bus bar;
at least one additional primary electrical equipment including a primary load and a bus bar switch, the primary load being coupled to the second power supply bus bar, and the bus bar switch being configured to selectively deactivate the second power supply bus bar downstream of the at least one additional primary electrical equipment; and
at least one additional tertiary electrical equipment including a tertiary load being coupled to the second power supply bus bar downstream of the at least one additional primary electrical equipment parallel to the primary load of the at least one additional primary electrical equipment,
wherein the at least one additional primary electrical equipment further includes a load monitoring device configured to monitor the power demand of the primary load of said at least one additional primary electrical equipment and to output a deactivation signal to the bus bar switch for selectively deactivating the second power supply bus bar downstream of the at least one additional primary electrical equipment, when the monitored power demand of the primary load of said at least one additional primary electrical equipment exceeds a primary threshold.

5. A hatrack of an aircraft, comprising:
a power management system comprising:
an electrical power supply input configured to be coupled to an electrical power supply;
a first power supply bus bar coupled to the power supply input;
at least one primary electrical equipment including a primary load and a bus bar switch, the primary load being coupled to the first power supply bus bar, and the bus bar switch being configured to selectively deactivate the first power supply bus bar downstream of the at least one primary electrical equipment; and
at least one tertiary electrical equipment including a tertiary load being coupled to the first power supply bus bar downstream of the at least one primary electrical equipment parallel to the primary load,
wherein the at least one primary electrical equipment further includes a load monitoring device configured to monitor the power demand of the primary load and to output a deactivation signal to the bus bar switch for selectively deactivating the first power supply bus bar downstream of the at least one primary electrical equipment, when the monitored power demand of the primary load exceeds a primary threshold,
wherein the primary electrical equipment is an oxygen mask deployment system, and
wherein the tertiary electrical equipment is a passenger reading light.

6. A method for managing power supply in an aircraft having a power management system of claim 1 , the method comprising:
operating the tertiary load of the tertiary electrical equipment;
monitoring the power demand of the primary load of the primary electrical equipment; and
selectively deactivating the first power supply bus bar downstream of the at least one primary electrical equipment, when the monitored power demand of the primary load exceeds a primary threshold, the primary threshold being zero.

Assignees

• Airbus Operations Gmbh

Inventors

• Scheffler Sebastian
• Leuenberger Frank

Classifications

• H02J2105/32

  for aircrafts · CPC title

• H02J4/00

  Circuit arrangements for mains or distribution networks not specified as AC or DC; Circuit arrangements for mains or distribution networks combining AC and DC sections or sub-networks (arrangements using intermediate DC-AC-DC conversion H02J1/002; arrangements using high-voltage DC [HVDC] links H02J3/36) · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H02J1/14 Primary

  Balancing load and power generation in DC networks · CPC title

• B64D2011/0053

  Cabin passenger reading lights · CPC title