DE102022204760A1 - Electrical arrangement for an aircraft - Google Patents

Abstract

An electrical arrangement (1; 1') for an aircraft (2; 2') comprises: a low-voltage system (10; 10') with a battery (100) and at least one consumer (101) which is connected to the battery (100) of the Low-voltage system (10; 10') is connected to be supplied with electrical power from the battery (100), a higher-voltage system (11; 11') with a battery (110) which has a higher electrical output voltage than the battery (100 ) of the low-voltage system (10; 10'), and at least one electric motor (111), by means of which a rotor (12) can be driven in order to generate thrust and/or lift and which is connected to the battery (110) of the higher-voltage system (11; 11 ') is connected to be supplied with electrical power from the battery (110), wherein the at least one consumer (101) of the low-voltage system (10; 10`) comprises a flight control device (102), and wherein the low-voltage system (10; 10 ') is separated from the higher voltage system (11; 11').

Description

The present disclosure relates in particular to an electrical arrangement for an aircraft and to an aircraft with such an electrical arrangement.

Aircraft are powered in a variety of configurations. Combustion engines, e.g. piston engines or gas turbine engines, enable long ranges and high speeds. Drives with one or more electric motors enable the use of sustainably generated energy and are sometimes particularly low-maintenance and quiet. Advances in battery technology are enabling ever wider areas of application for electric drives.

In the aviation sector, defects in components can have particularly serious consequences. It is therefore always desirable to create drives that are as safe as possible. In many cases, potential failures of certain components can be countered by using several redundant components. However, this usually also increases the complexity of the entire structure, and possibly also the total weight.

The WO 2019/145777 A1 For example, describes an electrical arrangement with redundant field coils so that the failure of a field coil can be compensated for.

The object of the present invention is to provide an improved electrical arrangement.

According to one aspect, an electrical arrangement for an aircraft is provided, comprising: a low-voltage system with a battery and at least one load connected to the battery of the low-voltage system in order to be supplied with electrical power from the battery, a higher-voltage system with a battery, which has a higher electrical output voltage than the battery of the low-voltage system, and with at least one electric motor by means of which a rotor can be driven in order to generate thrust and / or lift for the aircraft, the electric motor being connected to the battery of the higher-voltage system in order to to be supplied with electrical power from the battery. It is provided that the at least one consumer of the low-voltage system comprises a flight control device, and the low-voltage system is separated from the higher-voltage system.

This is based on the knowledge that supplying the potentially particularly safety-relevant and sensitive, at least one consumer of the low-voltage system via the battery with the relatively low output voltage enables significantly increased safety than, in comparison, supplying this at least one consumer via a DC-DC converter Higher voltage system battery. A defect, for example in the DC-DC converter or in another component of the higher-voltage system, could damage at least one consumer. If the flight control device is damaged by such a defect, this could result in particularly serious dangers. By separating the low-voltage system from the higher-voltage system, such risks can be minimized or even completely eliminated with a particularly simple solution. The battery of the low-voltage system has a sufficiently large capacity to supply the at least one consumer with power for its operation from takeoff to landing.

The low-voltage system is electrically separated from the higher-voltage system in such a way that no electrical power can be transferred from the higher-voltage system to the low-voltage system. The low-voltage system is galvanically isolated from the higher-voltage system, in particular with regard to the power-carrying lines, which transmit energy from the battery of the higher-voltage system to the electric motor. In particular, the low-voltage system is electromagnetically separated from the higher-voltage system. The circuits that are directly connected to the battery of the higher voltage system or are indirectly coupled to it are completely separated from the circuits of the low voltage system (in particular also spaced apart).

It can be provided that the battery of the low-voltage system has an electrical output voltage of less than 100 V, in particular less than 50 V. Optionally, the electrical output voltage of the battery of the low-voltage system is a low voltage. The low-voltage system in particular provides a direct voltage as an output voltage. The battery includes several battery cells and optional electronics. The output voltage of the battery is, in particular, the nominal voltage of the battery.

The battery of the higher-voltage system can have an electrical output voltage of over 100 V, in particular over 300 V. Optionally, it is a voltage of over 1000 V. The higher-voltage system in particular provides a direct voltage as the output voltage. The battery of the higher voltage system tems includes several battery cells and optional electronics. The output voltage of the battery of the higher voltage system is in particular the nominal voltage of the battery. The battery of the higher voltage system has, for example, a larger number of battery cells than the battery of the low voltage system.

By means of the flight control device, for example, the at least one electric motor can be controlled directly or indirectly, for example via a motor control.

The flight control device includes, for example, or consists of avionics and/or a flight control computer. Optionally, the flight control device includes a navigation system. These components are particularly sensitive and important for a safe flight.

Optionally, the higher voltage system includes a DC-DC converter. It can be provided that an additional drive train component is connected to the battery of the higher voltage system via the DC-DC converter in order to be supplied with electrical power by this battery.

According to a further development, the DC-DC converter is designed to convert the electrical output voltage of the higher-voltage battery into a lower voltage. This means that low-voltage components, e.g. those that have a lot of redundancy, can be supplied with power via the battery of the higher-voltage system.

The converted lower voltage may be the same (or approximately the same) as the electrical output voltage of the battery of the low voltage system. This enables the use of standard components.

In an alternative (or additional) embodiment, a powertrain component is connected to the battery of the low voltage system to be supplied with electrical power from the battery. This means that this drive train component can also be operated with a particularly high degree of safety.

The drive train component includes in particular electronic components.

The higher voltage system battery may have a larger number of battery cells connected in series than the low voltage system battery to achieve the higher voltage.

The rotor includes, for example, several rotor blades. For example, the rotor is a propeller or a fan.

Optionally, the electrical arrangement comprises a plurality of higher-voltage systems, each with a battery which has a higher electrical output voltage than the battery of the low-voltage system, and at least one electric motor, by means of which a rotor can be driven in order to generate thrust and/or lift, and the the battery of the higher voltage system is connected to be supplied with electrical power by the battery, the low voltage system being separated from each of the higher voltage systems.

According to one aspect, an aircraft is provided comprising the electrical arrangement according to any embodiment described herein. The electrical arrangement generates thrust and/or lift for the aircraft. The advantages mentioned above are particularly noticeable in an aircraft.

• 1 ein Luftfahrzeug in Form eines Flugzeugs mit einem elektrisch angetriebenen Rotor;
• 2 ein Luftfahrzeug in Form eines VTOL-Flugzeugs mit mehreren elektrisch angetriebenen Rotoren;
• 3 eine elektrische Anordnung des Luftfahrzeugs gemäß 1 und für das Luftfahrzeug gemäß 2;
• 4 eine alternativ ausgebildete elektrische Anordnung für das Luftfahrzeug gemäß 1 und gemäß 2; und
• 5 eine elektrische Anordnung mit mehreren Höherspannungssystemen für das Luftfahrzeug gemäß 2.

Embodiments will now be described by way of example with reference to the figures; in the figures show in schematic representations:

• 1 an aircraft in the form of an airplane with an electrically driven rotor;
• 2 an aircraft in the form of a VTOL aircraft with multiple electrically powered rotors;
• 3 an electrical arrangement of the aircraft according to 1 and for the aircraft according to 2 ;
• 4 an alternatively designed electrical arrangement for the aircraft 1 and according to 2 ; and
• 5 an electrical arrangement with several higher voltage systems for the aircraft 2 .

1 shows an aircraft 2 in the form of an electrically powered aircraft with a fuselage 20 and wings 21.

The aircraft 2 includes an electrical arrangement with a rotor 12 which is driven by an electric motor. The rotor 12 comprises several, here as an example two rotor blades 121. In the example shown, the rotor blades 121 are mounted on a hub and thus form a propeller. In alternative embodiments, the aircraft 2 includes a fan instead of a propeller and/or several electrical arrangements, each with at least one propeller or fan.

2 shows an aircraft 2 'that has several rotors 12. In the present case, the aircraft 2' is designed, for example, as a VTOL aircraft, specifically as a VTOL aircraft. Vertical take-off and landing aircraft, such as airplanes, are regularly referred to as VTOL aircraft, with the abbreviation VTOL being derived from “Vertical Take-Off and Landing”. VTOL aircraft are trained for vertical takeoff and landing. A VTOL aircraft particularly benefits from the advantages of the electrical arrangements described herein. The aircraft 2' includes several electrical arrangements as explained below 3 , alternatively or additionally according to those explained below 4 , alternatively or additionally an electrical arrangement according to 5 .

3 shows an electrical arrangement 1 for an aircraft, specifically the electrical arrangement of the aircraft 2 according to 1 . The electrical arrangement 1 includes a low-voltage system 10 and a higher-voltage system 11. The low-voltage system 10 is, for example, a low-voltage system, which can also be referred to as an LV system. The higher-voltage system 11 is, for example, a high-voltage system that can also be referred to as an HV system.

The low-voltage system 10 includes a battery 100 and at least one consumer 101. The consumer 101 is connected to the battery 100 of the low-voltage system 10 in order to be supplied with electrical power by the battery 100.

The higher-voltage system 11 also includes a battery 110. This battery 110 has a higher electrical output voltage than the nominal voltage than the battery 100 of the low-voltage system 10. Furthermore, the higher-voltage system 11 includes at least one electric motor 111. The rotor 12 can be driven by means of the electric motor 111 to provide thrust and/or to generate lift of the aircraft 2. The electric motor 111 is connected to the battery 110 of the higher voltage system 11 to be supplied with electrical power by the battery 110 and to generate thrust and/or lift.

It is provided that the at least one consumer 101 of the low-voltage system 10 includes a flight control device 102. Furthermore, it is provided that the low-voltage system 10 is electrically separated from the higher-voltage system 11 (specifically: galvanically isolated). This is in 3 illustrated by a dashed line. The low voltage system 10 is separated from the higher voltage system 11 with respect to electrical interactions. The low voltage system 10 is isolated from the higher voltage system 11. No energy can be exchanged between the low voltage system 10 and the higher voltage system 11. Between the low-voltage system 10 and the higher-voltage system 11 there is no electrically conductive connection and no energy-transmitting coupling (eg via a transformer or the like). An optional exchange of signals (communication) between the low-voltage system 10 and the higher-voltage system 11 also takes place electrically separately and/or via commercially available signal lines (eg network cables), via which no substantial electrical energy can be transferred.

The low voltage system 10 and the higher voltage system 11 are completely electrically isolated from one another. The low-voltage system 10 and the higher-voltage system 11 are galvanically isolated from one another. The circuits of the low voltage system 10 and the circuits of the higher voltage system 11 are electrically isolated from each other. In the present case, the low-voltage system 10 and the higher-voltage system 11 are separated from one another in such a way that there is no magnetic coupling, for example via a transformer or the like. The low voltage system 10 and the higher voltage system 11 are independent of each other.

The nominal voltage of the battery of the low-voltage system 10 is lower than the nominal voltage of the battery of the higher-voltage system 11. The battery 100 of the low-voltage system 10 in the present case has an electrical output voltage of less than 100 V, namely less than 50 V, specifically between 20 and 30 V (im shown example of 28 V). The battery 110 of the higher voltage system 11, in contrast, has an electrical output voltage of over 100 V, in particular of over 300 V, specifically over 500 V. In the battery 110 of the higher voltage system 11, a larger number of battery cells are connected in series than in the battery 100 of the low-voltage system 10. The circuit(s) of the higher-voltage system 11, which are supplied by the electrical output voltage of the battery 110 of the higher-voltage system 11 and/or carry this output voltage, are electrically (and magnetically) separated from the low-voltage system 10 (and spaced therefrom and in particular not coupled via a transformer or the like, i.e. generally not actively connected).

By means of the flight control device 102, for example, the at least one electric motor 111 is directly or indirectly controllable. Specifically, the flight control device 102 includes avionics (and/or a flight control computer). The flight control device 102 has flight control functions and/or a navigation function. In the present case, the flight control device 102 includes a navigation system. Furthermore, the flight control device 102 is (optionally) set up to read out and process sensor data. For example, the flight control device 102 controls rudders, and/or tail units and/or an engine control, for example based on inputs from a pilot and/or on the sensor data. The signals for this are sent, for example, via optical elements such as optical fibers. In particular, signal lines via which signals can be transmitted between the low-voltage system 10 and the higher-voltage system 11 each have a galvanic isolation, for example via one or more optocouplers. For example, an insulation barrier is provided between the low-voltage system 10 and the higher-voltage system 11. The low voltage system 10 is electrically isolated from the higher voltage system 11 with respect to (optional) signal lines. In particular, a communication network of the electrical arrangement 1, which communicatively connects the low-voltage system 10 to the higher-voltage system 11, is electrically separated from a power voltage network of the higher-voltage system 11.

The electrical arrangement 1 further comprises a DC-DC converter 13 and (at least) one drive train component 14. In the example shown, the drive train component 14 (optionally) represents the entire low-voltage system of the drive train.

The drive train component 14 is electrically connected to the battery 110 of the higher voltage system 11 via the DC-DC converter 13 in order to be supplied with electrical power by the battery 110. The DC-DC converter 13 converts a higher DC voltage into a lower DC voltage and provides the lower DC voltage to the powertrain component 14. This lower DC voltage is, for example, as high as the DC voltage of the battery of the low-voltage system 10.

The powertrain component 14 includes electronic components. The drive train component 14 is, for example, in communicative connection with the flight control device 102. In the present case, the drive train component 14 is the engine control. The engine control controls the electric motor 111.

By separating the low-voltage system 10 from the higher-voltage system 11, the at least one consumer 101 is protected from any defects in the higher-voltage system 11.

4 shows an electrical arrangement 1' for each of the aircraft 2, 2'. The electrical arrangement 1' in turn comprises a low-voltage system 10' and a higher-voltage system 11'.

The low-voltage system 10 'has an analogous structure to the electrical arrangement 1 described above 3 a battery 100 and a consumer connected to it with a flight control device 102. In addition, the powertrain component 14 is also connected to the battery 100 of the low voltage system 10 to be supplied with electrical power from the battery 100. In the example of 4 All systems of the aircraft (in particular all systems permanently installed in the aircraft), which are operated with a lower voltage compared to the higher voltage system 11 ', are separated from the higher voltage system 11' and (optionally) electrically coupled to the low voltage system 10.

In the higher-voltage system 11', the electric motor 111 is in turn driven by energy from the battery 110 of the higher-voltage system 11'.

The drive train component 14 can also be protected from defects in the higher voltage system 11'.

A further advantage of the electrical arrangement 1' is that electromagnetic interference between the individual low-voltage components can be reduced because a converter can be dispensed with.

5 shows another electrical arrangement, specifically for the aircraft 2 'according to 2 . This electrical arrangement is like the electrical arrangement 1 according to 3 designed, the drive arrangement according to 5 In contrast, it includes several parallel higher voltage systems 11, each one for one or more electric motors 111.

The flight control device 102 controls the engine controls of the drive train components 14 of the individual higher voltage systems 11.

If there is a defect in one of the higher voltage systems 11, the low voltage system 10 remains protected. The flight control device 102 and the other higher voltage systems 11 remain intact.

Likewise, with the electrical arrangement 1 'according to 4 (analogous to the electrical arrangement according to 5 ) several higher voltage systems 11 'can be provided.

Optionally (in any electrical arrangement described herein) are a plurality of redundant low voltage systems 10; 10' provided.

Reference symbol list

1; 1'

electrical arrangement

10; 10'

Low voltage system

100

battery

101

consumer

102

Flight control device

11; 11'

Higher voltage system

110

battery

111

Electric motor

12

rotor

121

Rotor blade

13

DC-DC converter

14

Powertrain component

2; 2'

aircraft

20

hull

21

wing

QUOTES INCLUDED IN THE DESCRIPTION

This list of documents listed by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• WO 2019145777 A1 [0004]

Claims (14)

Electrical arrangement (1; 1') for an aircraft (2; 2'), comprising: - a low-voltage system (10; 10') with a battery (100) and at least one consumer (101) which is connected to the battery (100) of the low-voltage system (10; 10') in order to be supplied with electrical power from the battery (100). to be supplied with electricity, - a higher-voltage system (11; 11') with a battery (110), which has a higher electrical output voltage than the battery (100) of the low-voltage system (10; 10'), and at least one electric motor (111), by means of which a rotor ( 12) can be driven to generate thrust and/or buoyancy, and which is connected to the battery (110) of the higher voltage system (11; 11') in order to be supplied with electrical power by the battery (110), the at least a consumer (101) of the low-voltage system (10; 10`) comprises a flight control device (102), and wherein the low-voltage system (10; 10') is separated from the higher-voltage system (11; 11'). Electrical arrangement (1; 1') according to Claim 1 , wherein the battery (100) of the low-voltage system (10; 10') has an electrical output voltage of less than 100 V, in particular less than 50 V. Electrical arrangement (1; 1') according to Claim 1 or 2 , wherein the battery (110) of the higher voltage system (11; 11') has an electrical output voltage of over 100 V, in particular over 300 V. Electrical arrangement (1; 1') according to one of the preceding claims, wherein the at least one electric motor (111) can be controlled directly or indirectly by means of the flight control device (102). Electrical arrangement (1; 1') according to one of the preceding claims, wherein the flight control device (102) comprises or consists of avionics and/or a flight control computer. Electrical arrangement (1) according to one of the preceding claims, wherein a drive train component (14) is connected to the battery (110) of the higher voltage system (11; 11 ') via a DC-DC converter (13) in order to be supplied with electrical power from the battery (110). to be taken care of. Electrical arrangement (1) according to Claim 6 , wherein the DC-DC converter (13) is designed to convert the electrical output voltage of the high-voltage battery (110) into a lower voltage. Electrical arrangement (1) according to Claim 7 , wherein the converted lower voltage is the same as the electrical output voltage of the battery (100) of the low-voltage system (10; 10 '). Electrical arrangement (1 ') according to one of Claims 1 until 5 , wherein a powertrain component (14) is connected to the battery (100) of the low-voltage system (10; 10 ') to be supplied with electrical power from the battery (100). Electrical arrangement (1; 1') according to one of Claims 6 until 9 , wherein the drive train component (14) comprises electronic components. Electrical arrangement (1; 1') according to one of the preceding claims, wherein a larger number of battery cells are connected in series in the battery (110) of the higher voltage system (11; 11') than in the battery (100) of the low voltage system (10; 10'). Electrical arrangement (1; 1') according to one of the preceding claims, wherein the rotor (12) comprises a plurality of rotor blades (121). Electrical arrangement (1; 1') according to one of the preceding claims, comprising a plurality of higher-voltage systems (11; 11'), each with a battery (110) which has a higher electrical output voltage than the battery (100) of the low-voltage system (10; 10 '), and at least one electric motor (111), by means of which a rotor (12) can be driven in order to generate thrust and/or lift, and which is connected to the battery (110) of the higher-voltage system (11; 11'), in order to to be supplied with electrical power from the battery (110), the low voltage system (10; 10') being separated from each of the higher voltage systems (11; 11'). Aircraft (2; 2'), comprising the electrical arrangement (1; 1') according to one of the preceding claims.

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