System for redundant supply of kinetic energy to drive system of aircraft

Patent metadata

Field	Value
Publication number	US-10787271-B2
Application number	US-201615744329-A
Country	US
Kind code	B2
Filing date	Jun 28, 2016
Priority date	Jul 13, 2015
Publication date	Sep 29, 2020
Grant date	Sep 29, 2020

Abstract

The invention relates to the redundant supply of kinetic energy to a drive system of an aircraft in order to ensure in each case largely safe operation of the aircraft during normal operation of the system and also in various emergency scenarios. The system has two electrical machines (110, 130), each of which is connected to in each case one of the two propellers. A high-voltage battery (120) and an internal combustion engine (140) are also provided. These components of the system are, depending on the type of component, electrically and/or mechanically connected to one another and to the propellers, and a controller of the system controls energy flows between the components depending on the mode of operation or readiness for operation of the components in a redundant manner in such a way that the aircraft can be largely safely operated in various normal and emergency situations.

First claim

The invention claimed is:

1. A system for providing kinetic energy for a drive system of an aircraft, the system comprising:
a first electrical machine and a second electrical machine, each of the first electrical machine and the second electrical machine configured to operate as a generator or an electric motor;
an HV battery configured to provide electrical energy;
a combustion engine configured to provide kinetic energy; and
a control system configured to control flows of kinetic, electrical, or kinetic and electrical energy between the first electrical machine, the second electrical machine, the HV battery, and the combustion engine based on an operating state of the system;
wherein the first electrical machine and the second electrical machine are connected mechanically to the drive system to provide kinetic energy to the drive system;
wherein the second electrical machine is electrically connectable to the first electrical machine, such that the second electrical machine is configured to provide electrical energy to the first electrical machine;
wherein the second electrical machine is electrically connected to the HV battery to transfer electrical energy from the second electrical machine to the HV battery or to transfer electrical energy from the HV battery to the second electrical machine,
wherein the HV battery is electrically connected to the first electrical machine, the combustion engine is mechanically connectable to the drive system to provide kinetic energy to the drive system, and the combustion engine is mechanically connectable to the second electrical machine to provide kinetic energy to the second electrical machine,
wherein the control system is configured to control the system in a first normal operational state, in which a momentary charge state of the HV battery corresponds at least to a predetermined nominal charge state, such that a first portion of the kinetic energy provided by the combustion engine is transferrable to the drive system, a second portion of the kinetic energy provided by the combustion engine is transferred to the second electrical machine, and the second electrical machine functions as a generator and converts the kinetic energy transferred from the combustion engine into electrical energy and provides the electrical energy,
wherein all of the electrical energy provided by the second electrical machine is supplied to the first electrical machine, and
wherein the first electrical machine functions as an electric motor and converts the electrical energy supplied by the second electrical machine into kinetic energy that is suppliable to the drive system.

2. The system of claim 1 , further comprising:
a main battery configured to supply electrical consumers of the aircraft, wherein the main battery is electrically connected to the HV battery, the second electrical machine, or the HV battery and the second electrical machine, such that the main battery is chargeable.

3. The system of claim 2 , wherein the control system is configured to control the system in an emergency mode in which the first electrical machine, the second electrical machine, the HV battery, the main battery, or lithe combustion engine, or any combination thereof is faulty, such that:
the first electrical machine, the second electrical machine, or the first electrical machine and the second electrical machine function as an electric motor, and
the main battery supplies electrical energy to the first electrical machine, the second electrical machine, or the first electrical machine and the second electrical machine functioning as an electric motor, and the electrical energy supplied by the main battery is converted into kinetic energy in the respective electrical machine, and
wherein the first electrical machine, the second electrical machine, or the first electrical machine and the second electrical machine working as an electric motor, respectively, is connectable mechanically to the drive system, and the respective converted kinetic energy is suppliable by the mechanical connections to the drive system.

4. The system of claim 2 , wherein the control system is configured to control the system in an emergency mode with a faulty main battery such that an onboard network of the aircraft is supplied with electrical energy from the HV battery, the second electrical machine working as a generator, or the HV battery and the second electrical machine working as a generator.

5. The system of claim 2 , wherein the control system is configured to control the system in an emergency mode with a faulty HV battery such that:
a first portion of the kinetic energy provided by the combustion engine is transferrable to the drive system,
a second portion of the kinetic energy provided by the combustion engine is transferred to the second electrical machine, and
the second electrical machine functions as a generator and converts the kinetic energy transferred from the combustion engine into electrical energy and provides electrical energy,
wherein the electrical energy provided by the second electrical machine is supplied to the first electrical machine, and
wherein the first electrical machine functions as an electric motor and converts the electrical energy supplied by the second electrical machine into kinetic energy that is supplied to the drive system.

6. The system of claim 2 , wherein the control system is configured to control the system in an emergency mode with a faulty first electrical machine such that the kinetic energy provided by the combustion engine is transferred entirely to the drive system.

7. The system of claim 2 , wherein the control system is configured to control the system in an emergency mode with a faulty second electrical machine such that the kinetic energy provided by the combustion engine is transferred entirely to the drive system and electrical energy provided by the HV battery is supplied entirely to the first electrical machine, and
wherein the first electrical machine functions as an electric motor and converts the electrical energy supplied by the HV battery into kinetic energy that is supplied to the drive system.

8. The system of claim 2 , wherein the control system is configured to control the system in an emergency mode with a faulty combustion engine such that a first portion of the electrical energy provided by the HV battery is supplied to the first electrical machine,
wherein the first electrical machine functions as an electric motor and converts the electrical energy supplied by the HV battery into kinetic energy that is suppliable to the drive system, and a second portion of the electrical energy provided by the HV battery is supplied to the second electrical machine, and
wherein the second electrical machine functions as an electric motor and converts the electrical energy supplied by the HV battery into kinetic energy that is suppliable to the drive system.

9. The system of claim 2 , wherein the control system is configured to control the system in a second normal operational state, in which a momentary charge state of the HV battery is lower than a predetermined nominal charge state, such that a first portion of the kinetic energy provided by the combustion engine is transferred to the drive system, a second portion of the kinetic energy provided by the combustion engine is transferred to the second electrical machine, and the second electrical machine functions as a generator and converts the kinetic energy transferred from the combustion engine into electrical energy and provides the electrical energy,
wherein a part of the electrical energy provided by the second electrical machine-is supplied to the first electrical machine, and
wherein the first electrical machine functi

Assignees

• Siemens Ag
• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Barth Peter
• Braun Klaus
• Dünsbier Stefan

Classifications

• B64D35/025

  of parallel type · CPC title

• B64D27/34

  All-electric aircraft · CPC title

• B64D35/024

  of series type · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D31/18

  for hybrid-electric power plants · CPC title