High-voltage direct current power supply system for an aircraft

Patent metadata

Field	Value
Publication number	US-9873520-B2
Application number	US-201515500753-A
Country	US
Kind code	B2
Filing date	Jul 20, 2015
Priority date	Jul 31, 2014
Publication date	Jan 23, 2018
Grant date	Jan 23, 2018

Abstract

The invention provides an electrical power supply system for an aircraft, the system comprising: a first electrical power supply network ( 1 ) including a first alternator ( 10 ); a second electrical power supply network ( 2 ) including a second alternator ( 20 ); and secondary lines ( 40 ) united in at least a first group ( 41 ) such that they are connected via switches to a common first intermediate line ( 51 ), and in at least a second group ( 42 ) so as to be connected via switches to a common second intermediate line ( 52 ); the system including a control member ( 60 ) for controlling the electrical power supply networks, the control member being arranged to servo-control each of the alternators in current, the system being arranged in such a manner that the power supply outputs of the two electrical power supply networks are connected together prior to being connected to each intermediate line, each intermediate line thus being powered in parallel by the two electric power supply networks.

First claim

The invention claimed is:

1. A high voltage direct current electrical power supply system for an aircraft, the system comprising at least:
a first electrical power supply network including a first alternator;
a second electrical power supply network including a second alternator; and
secondary lines for electrically powering elements of the aircraft,
wherein the secondary lines are united in at least a first group so as to be connected via switches to a common first intermediate line, and in at least a second group so as to be connected via switches to a common second intermediate line; and
wherein the system includes a control member for controlling the electrical power supply networks, the control member being arranged to servo-control each of the alternators in current, the system being arranged in such a manner that first power supply outputs of the two electrical power supply networks are connected together prior to being connected to the first intermediate line and so that second power supply outputs of the two electrical power supply networks, distinct from the first outputs, are connected together prior to being connected to the second intermediate line, each intermediate line thus being powered by the two electrical power supply networks and the two intermediate lines being powered in parallel.

2. The system according to claim 1 , wherein the control member includes reception means for receiving a distribution setpoint for the electrical power to be supplied to the intermediate line by each electrical power supply network and for receiving a measurement of voltage across the terminals of at least one of the intermediate lines, the control member being configured to generate current control setpoints for each of the alternators as a function of said distribution setpoints and of said voltage measurement.

3. The system according to claim 2 , wherein the control member also includes detector means for detecting excess voltage in each of the electrical power supply networks and in communication with the control member.

4. The system according to claim 2 , wherein the reception means decouple the distribution setpoint into a first setpoint for the first network and a second setpoint for the second network.

5. The system according to claim 4 , wherein the control member has two multipliers, the first multiplier being configured to multiply the first setpoint by an error between the voltage measurement and a threshold voltage, and the second multiplier being configured to multiply the second setpoint by said error between the voltage measurement and the threshold voltage.

6. The system according to claim 5 , wherein the control member includes a first voltage-to-current converter connected to the output from the first multiplier, and a second voltage-to-current converter connected to the output of the second multiplier.

7. The system according to claim 1 , wherein each electrical power supply network comprises one of the first or the second alternators, a rectifier connected to the first or the second alternator, a lowpass filter connected to the rectifier, and at least two switches connected in parallel to the lowpass filter, the outputs from the switches being connected to respective ones of the intermediate lines.

8. The system according to claim 1 , wherein one of the alternators is connected to an auxiliary power unit of the aircraft.

9. The system according to claim 1 , having three electrical power supply networks, each having an alternator, the secondary lines being united in three groups, each connected to a common intermediate line via switches, the system being arranged in such a manner that each intermediate line is powered in parallel by each of the three electrical power supply networks.

Assignees

• Safran Electronics & Defense

Inventors

• Guillot François

Classifications

• H02J2105/32

  for aircrafts · CPC title

• H02J1/08 Primary

  Three-wire DC power distribution systems; Systems having more than three wires · CPC title

• H02J3/381

  Dispersed generators · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H02J1/00

  Circuit arrangements for DC mains or DC distribution networks · CPC title