Electrical control system

Patent metadata

Field	Value
Publication number	US-2016355275-A1
Application number	US-201514624877-A
Country	US
Kind code	A1
Filing date	Feb 18, 2015
Priority date	Feb 18, 2015
Publication date	Dec 8, 2016
Grant date	—

Abstract

An example aircraft electrical system includes a generator coupled with a gas turbine engine and a controller operable to distribute power of the generator. The controller includes a first control module positioned at a first location remote from the generator and a second control module positioned at a second location proximate the generator. The first control module is configured to verify at least one output of the generator, detect a fault condition of the generator, and control operation of at least one power bus in communication with the first control module. The second control module is configured to regulate the at least one output of the generator, where the at least one output includes a voltage. An example method of operating an electrical system is also disclosed.

First claim

1 . An aircraft electrical system comprising:
a generator coupled with a gas turbine engine; and a controller operable to distribute power of the generator, the controller including,
a first control module positioned at a first location remote from the generator, the first control module being configured to verify at least one output of the generator, detect a fault condition of the generator, and control operation of at least one power bus in communication with the first control module, and
a second control module positioned at a second location proximate the generator and configured to regulate the at least one output of the generator, wherein the at least one output includes a voltage.

2 . The aircraft electrical system of claim 1 , wherein the second control module includes an exciter drive powered by an auxiliary power source.

3 . The aircraft electrical system of claim 1 , wherein the second control module has a first connector arranged to provide power from an auxiliary power source and a second connector, spaced from the first connector, and arranged to communicate at least one analog input to the second control module.

4 . The aircraft electrical system of claim 1 , wherein the first control module is in communication with the second control module and is operable to take the generator and the second control module offline in response to the fault condition.

5 . The aircraft electrical system of claim 1 , further including a generator line control in communication with the first control module and the second control module, wherein the generator line control receives power from the generator, wherein the generator line control is changed to an OFF state by either of the first control module and the second control module in response to the fault condition such that distribution of power from the generator ceases.

6 . The aircraft electrical system of claim 1 , further including a generator control relay in communication with the first control module and the second control module, wherein the generator control relay is configured to interrupt communication between an rectifier and an exciter drive of the second control module in response to a command from the first control module or the second control module.

7 . The aircraft electrical system of claim 1 , wherein the first control module and the second control module are each configured to electrically isolate the generator in response to the fault condition, wherein the fault condition includes at least one of an overvoltage condition, an undervoltage condition, an overfrequency condition, and an underfrequency condition.

8 . The aircraft electrical system of claim 1 , wherein the second control module is attached to the generator, or within the generator.

9 . The aircraft electrical system of claim 1 , wherein a processor of the second control module is in communication with an exciter drive of the second control module, wherein the second control module commands the exciter drive to increase or decrease excitation of the generator in response to a measurement of the voltage.

10 . The aircraft electrical system of claim 9 , wherein the processor commands the exciter drive to increase or decrease excitation of the generator in response to a measurement of a current from the generator.

11 . The aircraft electrical system of claim 1 , wherein the first control module monitors a plurality of system parameters including at least one of frequency, voltage, generator speed, or combinations thereof, and the first control module changes power provided by the at least one power bus in response to a change in at least one of the plurality of system parameters.

12 . A method of operating an aircraft electrical system including the steps of:
providing a generator coupled with a gas turbine engine and a controller including a first control module and a second control module; verifying an output of the generator with the first control module positioned at a first location remote from the generator, wherein the first control module is operable to detect a fault condition of the generator; regulating the output of the generator with a second control module positioned at a second location proximate the generator, wherein the second output includes a voltage; and controlling operation of at least one power bus with the first control module.

13 . The method of claim 12 , further comprising
communicating measurements of generator parameters to the first control module from the second control module; and taking the generator offline in response to a fault condition.

14 . The method of claim 12 , wherein the step of regulating a voltage includes a processor of the second control module communicating with an exciter drive of the second control module to command the exciter drive to increase or decrease excitation of the generator in response to a measurement of the voltage output of the generator.

15 . The method of claim 12 , further comprising powering the exciter drive of the second control module with an auxiliary power source.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Seger Mark J
• Ralph Wes
• Hoegberg Lon R
• Bayles Robert A
• Patel Sunil S

Classifications

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• H02P29/0241

  the fault being an overvoltage · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title