Electrical drive system for an aircraft and operating method

Patent metadata

Field	Value
Publication number	US-10035607-B2
Application number	US-201715441650-A
Country	US
Kind code	B2
Filing date	Feb 24, 2017
Priority date	Mar 2, 2016
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

An electrical drive system for an aircraft includes: at least one first and one second electrical direct voltage sources for supplying a direct voltage, and a first and a second electrical machine modules configured to convert electrical alternating voltage into mechanical movement and vice versa. The first and second modules are connected to a first and a second power inverters, respectively. The first and second inverters are connected in series and the first and the second direct voltage sources are connected in series to generate an overall direct voltage to which the inverters are connected. The power inverters each has one voltage measuring device for measuring the power inverter direct voltage present at the respective inverter and a power inverter control device for controlling the operation of the inverters in accordance with the power inverter direct voltage.

First claim

The invention claimed is:

1. An electrical drive system for an aircraft, comprising:
at least one first and one second electrical direct voltage source for supplying a direct voltage,
a first electrical machine module and a second electrical machine module, the electrical machine modules being configured to convert electrical alternating voltage into mechanical movement and/or to convert mechanical movement into electrical alternating voltage, the first electrical machine module being connected to a first power inverter and the second electrical machine module being connected to a second power inverter, the first and second power inverters being connected in series and the first and the second direct voltage sources being connected in series to generate an overall direct voltage to which the series-connected power inverters are connected, the power inverters each having one voltage measuring device for measuring the power inverter direct voltage present at the respective power inverter and a power inverter control device for controlling the operation of the power inverters in accordance with the power inverter direct voltage, a compensating line being provided between a voltage source center tap between the first and second voltage sources and a power inverter center tap between the first and second power inverters, and the first and second power inverter control devices being connected to each other communicatively by a communication device to exchange at least one piece of information about the measured power inverter direct voltages in real time; and
a compensating current measuring device for measuring the compensating current flowing through the compensating line, wherein a piece of information about the measured compensating current is configured to be transmitted via the communication device to at least one of the power inverter control devices.

2. The electrical drive system according to claim 1 , wherein at least one of the power inverters has a power inverter current measuring device for measuring the power inverter direct voltage current flowing through the power inverter, wherein a piece of information about the measured power inverter direct voltage current can be transmitted in real time via the communication device.

3. The electrical drive system according to claim 1 , wherein the first and/or the second power inverter is implemented in a machine control unit.

4. The electrical drive system according to claim 1 , wherein the first and second power inverter control devices are configured for compensating and/or adjusting the powers between the first and second direct voltage sources.

5. The electrical drive system according to claim 1 , further comprising at least one of:
at least one or several further direct voltage sources connected in series with the first and second direct voltage sources to generate the overall direct voltage, and/or
at least one or several further electrical machine modules with one further power inverter each, the further power inverter(s) being connected in series with the first and second power inverters and also having a further power inverter direct voltage measuring device and a further power inverter control device that are connected to the communication device.

6. The electrical drive system according to claim 1 , wherein the first and/or the second direct voltage source is provided with a voltage source switching device for switching off a terminal of the direct voltage source and with a bridging device for bridging the switched-off direct voltage source.

7. The electrical drive system according to claim 1 , wherein the compensating line is provided with a compensating line switching device with which the compensating line can be interrupted or connected.

8. The electrical drive system according to claim 1 , wherein the electrical machine modules are motor modules for driving a propulsion for an aircraft and/or for driving ancillary components of an aircraft.

9. The electrical drive system according to claim 1 , wherein the first and second direct voltage sources are selected from the group of direct voltage sources consisting of a battery, a battery pack, a rechargeable battery, a rechargeable battery pack, a fuel cell, a fuel cell array, a solar cell and a solar cell pack.

10. A method for operating an electrical drive system according to claim 1 , comprising:
compensating and/or adjusting the power distribution between the first and second direct voltage sources by the power inverter control devices.

11. An aircraft comprising an electrical drive system comprising:
at least one first and one second electrical direct voltage source for supplying a direct voltage,
a first electrical machine module and a second electrical machine module, the electrical machine modules being configured to convert electrical alternating voltage into mechanical movement and/or to convert mechanical movement into electrical alternating voltage, the first electrical machine module being connected to a first power inverter and the second electrical machine module being connected to a second power inverter, the first and second power inverters being connected in series and the first and the second direct voltage sources being connected in series to generate an overall direct voltage to which the series-connected power inverters are connected, the power inverters each having one voltage measuring device for measuring the power inverter direct voltage present at the respective power inverter and a power inverter control device for controlling the operation of the power inverters in accordance with the power inverter direct voltage, a compensating line being provided between a voltage source center tap between the first and second voltage sources and a power inverter center tap between the first and second power inverters, and the first and second power inverter control devices being connected to each other communicatively by a communication device to exchange at least one piece of information about the measured power inverter direct voltages in real time; and
a compensating current measuring device for measuring the compensating current flowing through the compensating line, wherein a piece of information about the measured compensating current can be transmitted via the communication device to at least one of the power inverter control devices.

Assignees

• Airbus Defence & Space Gmbh
• Airbus Operations Gmbh

Inventors

• Wangemann Joerg
• Schult Jens

Classifications

• B60L8/003

  Converting light into electric energy, e.g. by using photo-voltaic systems · CPC title

• B60L3/0092

  with use of redundant elements for safety purposes · CPC title

• B60L15/38

  with automatic control · CPC title

• B60L15/32

  Control or regulation of multiple-unit electrically-propelled vehicles · CPC title

• B60L50/15

  with additional electric power supply (with capacitors charged by engine-driven generators B60L50/40; with batteries charged by engine-driven generators B60L50/61) · CPC title