Electrical drive system for an aircraft and operating method

• US 10,035,607 B2
• Filed: 02/24/2017
• Issued: 07/31/2018
• Est. Priority Date: 03/02/2016
• Status: Active Grant

• Current Assignee: Airbus Defence and Space GmbH, Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Defence and Space GmbH, Airbus Operations GmbH (Airbus SE)
• Inventors: Wangemann, Joerg, Schult, Jens
• Primary Examiner(s): Chan, Kawing
• Application Number:
  US15/441,650
• Publication Number:
  US 20170253344A1
• Time in Patent Office: 522 Days
• Field of Search: 318440
• CPC Class Codes: B60L 1/003 to auxiliary motors, e.g. for pumps, compressors
• CPC Class Codes: B60L 15/007 Physical arrangements or structures of drive train converters specially adapted for the propulsion motors of electric vehicles
• CPC Class Codes: B60L 15/32 Control or regulation of multiple-unit electrically-propelled vehicles
• CPC Class Codes: B60L 15/38 with automatic control
• CPC Class Codes: B60L 2200/10 Air crafts
• CPC Class Codes: B60L 2210/42 Voltage source inverters
• CPC Class Codes: B60L 3/0092 with use of redundant elements for safety purposes
• CPC Class Codes: B60L 50/15 with additional electric power supply with capacitors charged by engine-driven generators B60L50/40; with batteries charged by engine-driven generators B60L50/61
• CPC Class Codes: B60L 50/51 characterised by AC-motors
• CPC Class Codes: B60L 50/66 Arrangements of batteries
• CPC Class Codes: B60L 50/90 using propulsion power supplied by specific means not covered by groups B60L50/10 - B60L50/50, e.g. by direct conversion of thermal nuclear energy into electricity
• CPC Class Codes: B60L 58/18 of two or more battery modules
• CPC Class Codes: B60L 58/19 Switching between serial connection and parallel connection of battery modules
• CPC Class Codes: B60L 58/20 having different nominal voltages
• CPC Class Codes: B60L 8/003 Converting light into electric energy, e.g. by using photo-voltaic systems
• CPC Class Codes: B60L 9/22 polyphase motors
• CPC Class Codes: B60L 9/30 fed from different kinds of power-supply lines
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: H02P 27/06 using dc to ac converters or inverters H02P27/05 takes precedence
• CPC Class Codes: Y02T 10/70 : Energy storage systems for electromobility, e.g. batteries
• CPC Class Codes: Y02T 10/7072 : Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
• CPC Class Codes: Y02T 10/72 : Electric energy management in electromobility

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.

Claims

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.