Simultaneous Bidirectional Power Usage of Generator Power Feeders

Patent metadata

Field	Value
Publication number	US-2020021111-A1
Application number	US-201816032290-A
Country	US
Kind code	A1
Filing date	Jul 11, 2018
Priority date	Jul 11, 2018
Publication date	Jan 16, 2020
Grant date	—

Abstract

Aircraft power distribution systems and methods for regulating a system voltage in aircraft power distribution systems are described. An example system includes a first generator, a first power feeder, a second power feeder, a first load, a second load, and a plurality of contactors. The first power feeder and the second power feeder are coupled in parallel between the first generator and a power panel. The first load is coupled to the first power feeder, and the second load is coupled to the second power feeder. The plurality of contactors is configurable to transfer power in a first direction from the first generator to both the first load and the second load during a first mode of operation, and configurable to transfer power in a second direction from the power panel to the first load or the second load during a second mode of operation.

First claim

What is claimed is:

1 . An aircraft power distribution system, comprising:
a first generator; a first power feeder coupled between the first generator and a power panel; a second power feeder coupled between the first generator and the power panel, the second power feeder coupled in parallel with the first power feeder; a first load coupled to the first power feeder; a second load coupled to the second power feeder; and a plurality of contactors, wherein each contactor of the plurality of contactors is connected to at least one of the first power feeder and the second power feeder, and
wherein the plurality of contactors is configurable to:
transfer power in a first direction from the first generator to both the first load and the second load during a first mode of operation, and
transfer power in a second direction from the power panel to the first load or the second load during a second mode of operation.

2 . The aircraft power distribution system of claim 1 , wherein, during the second mode of operation, the plurality of contactors are configured to transfer power from a second generator to the first load or the second load by way of the power panel.

3 . The aircraft power distribution system of claim 2 , wherein the first generator is an auxiliary power unit generator and the second generator is an engine generator.

4 . The aircraft power distribution system of claim 3 , wherein the first load is a wing ice protection system.

5 . The aircraft power distribution system of claim 3 , wherein the first load is an aft power distribution system.

6 . The aircraft power distribution system of claim 1 , wherein, during the second mode of operation, the plurality of contactors are configured to simultaneously transfer power in the second direction from the power panel to the second load and transfer power in the first direction from the first generator to the first load.

7 . The aircraft power distribution system of claim 1 , wherein the plurality of contactors are configured to transfer power in the second direction from the power panel to both the first load and the second load during a third mode of operation.

8 . The aircraft power distribution system of claim 7 , wherein, during the third mode of operation, the plurality of contactors are configured to transfer power from a second generator to both the first load and the second load by way of the power panel.

9 . The aircraft power distribution system of claim 7 , wherein, during the third mode of operation, the plurality of contactors are configured to transfer power from a second generator to the second load by way of the power panel and to transfer power from a third generator to the first load by way of the power panel.

10 . The aircraft power distribution system of claim 1 , further comprising a control unit configured to:
regulate a system voltage based on a first voltage at a first node when the first load is in use; and regulate the system voltage based on a second voltage at a second node when the first load is not in use.

11 . The aircraft power distribution system of claim 1 , further comprising a control unit configured to:
select either the first load or the power panel as a point of regulation; and regulate a system voltage based on a target voltage at the point of regulation.

12 . The aircraft power distribution system of claim 11 , wherein the control unit is configured to:
determine a state of one or more contactors of the plurality of contactors; and select the point of regulation based on the state of the one or more contactors.

13 . The aircraft power distribution system of claim 11 , wherein the control unit is configured to:
determine which direction current or power is flowing in the first power feeder; and select the point of regulation based on the direction that current or power is flowing in the first power feeder.

14 . The aircraft power distribution system of claim 1 , further comprising a control unit configured to:
monitor a first voltage at the first load and a second voltage at the power panel; and regulate a system voltage based on the first voltage, the second voltage, or both.

15 . A control system for regulating a system voltage in an aircraft power distribution system, the control system comprising:
first sensing equipment configured to sense a first voltage at a first node, wherein the first node comprises a load coupled to a power feeder between a generator and a power panel; second sensing equipment configured to sense a second voltage at a second node that is separate from the first node; and a control unit configured to:
select either the first node or the second node as a point of regulation;
determine a target voltage at the point of regulation; and
regulate the system voltage at the point of regulation based on the target voltage.

16 . The control system of claim 15 , wherein regulating the system voltage at the point of regulation based on the target voltage comprises adjusting an output current or power of the generator.

17 . The control system of claim 15 , wherein the control unit is further configured to:
determine whether or not the load is in use; and select, based on whether or not the load is in use, either the first node or the second node as the point of regulation.

18 . The control system of claim 15 , wherein the control unit is configured to determine the target voltage based on a voltage limit of the load, a voltage limit of a second load, or both.

19 . A method for regulating a system voltage in an aircraft power distribution system, the method comprising:
determining, by a control unit, whether or not a load is in use, wherein the load is coupled to a power feeder between a first generator and a power panel; selecting, by the control unit based on whether or not the load is in use, either a first node or a second node as a point of regulation, wherein the first node comprises the load, and wherein the second node is separate from the first node; determining, by the control unit, a target voltage at the point of regulation; and regulating, by the control unit, the system voltage at the point of regulation based on the target voltage.

20 . The method of claim 19 , wherein the aircraft power distribution system comprises a plurality of contactors configurable to vary a direction in which power is transferred in the power feeder, and wherein determining whether or not the load is in use comprises determining whether or not the load is in use based on a state of one or more of the plurality of contactors.

Assignees

• Boeing Co

Inventors

• White Jeffrey J

Classifications

• H02J9/068

  Electronic means for switching from one power supply to another power supply, e.g. to avoid parallel connection · CPC title

• H02J2105/30

  the load networks being external to vehicles, i.e. exchanging power with vehicles · CPC title

• G05F1/12 Primary

  wherein the variable actually regulated by the final control device is AC (G05F1/625 takes precedence) · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title