Electrical system for an aircraft

An electrical system for an aircraft is provided. The system comprises an inverter for transforming a first alternating current from an on-board network having a variable frequency into a second alternating current, and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current.

TECHNICAL FIELD

The technical field relates to an electrical system for an aircraft and a method, a computer program and a computer-readable medium for operating an electrical system of an aircraft.

BACKGROUND

Most aircraft comprise an electrical on-board network which is supplied with electrical energy by generators which are mechanically connected to engines of the aircraft. In order to save weight and to simplify the construction of an engine, for example a turbine, it is possible to dispense with a gear unit which has a transmission ratio and couples the generator with the engine and to directly connect the generator to the engine. This can lead to the on-board network frequency changing depending on the rotational speed of the engine. In this case, the on-board network of the aircraft is generally configured in such a way that it can be operated at a variable frequency. For example, a generator coupled directly with a turbine can produce a frequency of between 360 and 800 Hz, which is fed into the on-board network.

Many electrical loads in the aircraft, which for example include pumps or fans, are operated by electrical energy from the on-board network. Owing to the variable frequency, it may be necessary to decouple said loads by means of frequency converters.

In particular if motor-driven loads are to be operated at a desired rotational speed on an on-board network having a variable frequency, decoupling by means of direct current links and inverters may be necessary. This approach can, owing to the high network quality requirements, be very expensive and also relatively difficult, since complex filters and rectifier circuits (due to the high network quality requirements) may be used.

Examples of electrical loads of this type include fans for ventilation, as described in DE 10 2008 025 960 A1 and US 2011/0111683 A1. In addition, other objects, desirable features and characteristics will become apparent from the subsequent summary and detailed description, and the appended claims, taken in conjunction with the accompanying drawings and this background.

SUMMARY

Accordingly, it can be desirable to reduce the weight of an aircraft and to simplify the electrical system of an aircraft.

One of various aspects of the present disclosure relates to an electrical system for an aircraft. An electrical system may mean a plurality of electrical and electronic components of the aircraft which are interconnected via electrical lines. The electrical system may also comprise a control unit for these components.

According to an exemplary embodiment of the present disclosure, the system comprises an inverter for transforming a first alternating current from an on-board network having a variable first frequency into a second alternating current and at least a first electrical load and at least a second electrical load, which are configured to be operated simultaneously by the second alternating current.

At least two electrical loads may therefore be supplied with electrical energy by means of a single inverter. In this way, in the case of electrical loads which may be put into groups which achieve the same object, such as ventilators of an air-conditioning system, a large number of inverters may be dispensed with, and this may lead to a reduction in the weight of the aircraft.

The aircraft comprises an on-board network which is supplied by generators having a variable on-board network frequency. The alternating current having the variable on-board network frequency is converted by the converter into an alternating current which may be consumed by the electrical loads. For example, the electrical loads may comprise synchronous motors or asynchronous motors which are supplied with alternating current by the inverter simultaneously.

In general, an inverter comprises a rectifier for rectifying the first alternating current and a converter for producing the second alternating voltage from the direct current of the rectifier. In order, for example, to reduce the disturbances of the inverter to the on-board network, a 12-point rectifier may be used, which generally contains a transformer.

The electrical loads may each comprise an electric motor as a drive for a conveying device, by means of which a fluid, such as cabin air, may be conveyed together with the group of electrical loads. In general, it is possible in this way to use conventional, cheap and robust drive technology, in one example, where drives are in groups and only a single rotational speed or a rotational speed which may be commonly changed is required. Each plurality of motors of a group may be operated by just one inverter. The commonly used frequency may thus be considerably higher than the network frequency of the on-board network, and this may lead to saving on weight with the motors used.

Potential back reactions on the on-board network may only occur by means of the common inverter, which may reduce the overall complexity of the filter technology and monitoring measures to one place. This may lead to a lower total weight and lower costs on a system level.

According to an exemplary embodiment of the present disclosure, the electrical system further comprises a first load switch for disconnecting the first electrical load from the inverter and a second load switch for disconnecting the second electrical load from the inverter. Each of the electrical loads may be separately disconnected from the inverter via a load switch which is associated with the electrical load.

If an electrical load in a group fails, then the remaining electrical loads in the group may be operated at a somewhat higher frequency and the total capacity of the ventilation system is thus kept constant.

Asynchronous motors may also be directly connected to the inverter by switching elements or load switches.

This is also possible for synchronous motors, since it is possible via the control to restart after each configuration. If the rotational speed of all the motors connected to an inverter is monitored, a complete start-up may be dispensed with when using synchronous motors by the output frequency of the inverter being reduced until all the motors run synchronously again. This is possible since, for example in the case of fans, the load moment at low rotational speeds is very low.

According to an exemplary embodiment of the present disclosure, the inverter is a first inverter and the electrical system further comprises a second inverter and a collector line. It is further conceivable to have a redundancy of the inverter available, in order to be able to continue operating the individual electrical loads if the inverter or the supplying bar fails.

According to an exemplary embodiment of the present disclosure, the collector line connects the first inverter to the second inverter. In this way, all the electrical loads which are each connected to one inverter may also be supplied with current by the other inverter.

According to an exemplary embodiment of the present disclosure, the first electrical load and the second electrical load may be connected to the first inverter and the second inverter via the collector line. In one example, the individual loads may be disconnected from the collector line (for example an inverter bar) by a power circuit breaker (i.e. by a load switch), in order not to influence the availability of the remaining electrical loads if one electrical load fails.

According to another exemplary embodiment of the present disclosure, the electrical system further comprises a first collector line switch for disconnecting the first inverter from the collector line and/or a second collector line switch for disconnecting the second inverter from the collector line. If an inverter fails or experiences a disturbance, it may be disconnected from the collector line.

According to an exemplary embodiment of the present disclosure, the electrical system further comprises a third collector line switch for disconnecting a first part of the collector line, which is connected to the first inverter, from a second part of the collector line, which is connected to the second inverter. A first group of electrical loads may be connected to the first part of the collector line, and a second group of electrical loads may be connected to the second part of the collector line. These two groups may be disconnected from one another and also interconnected by means of the third collector line switch. In this way, the first group and the second group may each be disconnected from one another by the first inverter and may be supplied with current by the second inverter. It is, however, possible for two groups to be commonly supplied with current by just one inverter respectively or for two groups to be commonly supplied with current by two inverters.

According to an exemplary embodiment of the present disclosure, at least the first electrical load may be connected to the first part of the collector line and/or at least the second electrical load may be connected to the second part of the collector line. This may, for example, take place via a load switch.

According to an exemplary embodiment of the present disclosure, the electrical system further comprises a control unit which is configured to control the (first and second) inverter(s) in such a way that an adjustable output frequency is produced for the second alternating current and/or said control unit is configured to control switches of the system and to open and/or close said switches. Opening and closing the switches and adjusting the frequency of the second alternating current in the collector line may take place completely automatically by means of the control unit.

It is, however, possible for the switches, for example the collector line switches and/or the load switches, to be controlled manually and to be, for example, purely mechanical switches. These could be used during maintenance or for maintaining airworthiness after failure of a system part.

According to an exemplary embodiment of the present disclosure, the first electrical load comprises a first motor and the second electrical load comprises a second motor. In one example, in a group of motors, a common rotational speed may be set for the motors having the frequency of the second alternating voltage.

Both asynchronous motors of a conventional construction and synchronous motors, which are used for example in inverter drives due to the greater efficiency thereof, are used as the motors. This is possible since all the motors in a group may be started up together from the idle state. Potential differences in rotational speed within the group may also be taken into account by a suitable selection of the number of pairs of poles in a motor.

According to another exemplary embodiment of the present disclosure, the first electrical load comprises a first conveying device and the second electrical load comprises a second conveying device. As already mentioned, the electrical loads may be put into groups which achieve the same object at the same time, such as conveying a fluid. The conveying devices may be, for example, fans or ventilators connected in parallel or pumps connected in parallel.

For example, in the case of a ventilation system of an aircraft, a plurality of fans are respectively interconnected in groups which are logical in terms of ventilation.

Another exemplary aspect of the present disclosure relates to an aircraft, for example an airplane, and in one example, a passenger airplane, the cabin of which may be supplied with air for example by an air-conditioning system which comprises a large number of fans.

According to an exemplary embodiment of the present disclosure, the aircraft comprises a generator, which is mechanically coupled with a drive of the aircraft, for supplying an on-board network of the aircraft with electrical energy and comprises an electrical system as described above and below. The electrical system is generally only coupled with the on-board network via at least one inverter.

Another exemplary aspect of the present disclosure relates to a method for operating an electrical system of an aircraft which may be carried out by a control unit with the electrical system.

According to an exemplary embodiment of the present disclosure, the method comprises transforming an alternating current from an on-board network having a variable first frequency into a second alternating current having a second frequency and operating at least one first electrical load and at least one second electrical load with the second alternating current. As already mentioned, a plurality of electrical loads may be supplied with an alternating voltage by a single electrical inverter.

According to an exemplary embodiment of the present disclosure, the method further comprises determining a common conveying capacity of a first and a second conveying device and operating the electrical loads in such a way that the first and second conveying devices provide the common conveying capacity. For example, a group of motors having the same rotational speed may be operated.

According to an exemplary embodiment of the present disclosure, the method further comprises changing the second frequency of the second alternating current depending on the common conveying capacity. The rotational speed of the motors may be set by the second frequency.

According to an exemplary embodiment of the present disclosure, the method further comprises switching on the first and the second motor depending on the common conveying capacity. It is also possible for the motors always to be operated at the same rotational speed, the number of motors which are running being determined depending on the output.

It is also possible for the rotational speed of the motors and the number of running motors to be set at the same time.

According to an exemplary embodiment of the present disclosure, the method further comprises transforming the alternating current from the on-board network by means of a first inverter, disconnecting the first inverter from the first and the second electrical load, connecting a second inverter to the first and the second electrical load and transforming the alternating current from the on-board network by means of the second inverter.

If the first inverter or a generator coupled with the first inverter fails or malfunctions, the second inverter may take over the role of the first inverter. For example, the first inverter may be disconnected from the collector line or bus bar by means of the first collector line switch and the second inverter may be connected to the collector line by the second collector line switch. A first group of electrical loads, which were initially connected to the first inverter via a first part of the collector line, may be connected to the second inverter by closing the third collector line switch, which second inverter may then operate the first group of electrical loads.

Further exemplary aspects of the present disclosure relate to a computer program which, when executed on a processor, instructs the processor to carry out the method as described above and below, and to a computer-readable medium on which a computer program of this type is stored. A computer-readable medium may comprise, for example, a RAM, a ROM, an EPROM, a FLASH memory, a floppy disk, a CD, a DVD or a hard drive.

Another exemplary aspect of the present disclosure relates to a control unit or a control system for the electrical system, which is configured to carry out the method as described above and below. Said control unit may for example comprise a processor which is configured to execute the above-mentioned computer program, and a non-volatile memory as a computer-readable medium on which said program is stored.

A person skilled in the art can gather other characteristics and advantages of the disclosure from the following description of exemplary embodiments that refers to the attached drawings, wherein the described exemplary embodiments should not be interpreted in a restrictive sense.

DETAILED DESCRIPTION

FIG. 1shows an aircraft10in the form of a passenger aircraft10which comprises two turbines12a,12bas drives. Generators14a,14bare mechanically coupled with the turbines12a,12band feed electric current into an on-board network16of the aircraft10during operation of the turbines12a,12b. Depending on the operational state of the turbines, the generators14a,14bmay produce a variable network frequency of between about 360 and about 800 Hz in the on-board network16.

A plurality of electrical loads20is connected to the on-board network16. An electrical system22, which comprises an inverter18a,18bwhich is coupled with the on-board network16and a plurality of electrical loads24a,24b,24c,24d, which are supplied by the inverter18a,18b, is also connected to the on-board network16.

As shown inFIG. 1, the two inverters18a,18bmay be located at different points in the aircraft10for safety reasons, for example on the left-hand and the right-hand side thereof.

FIG. 2shows the electrical system22in greater detail. A first inverter18ais connected to a first generator12avia the on-board network16. The first inverter18ais configured to convert the first variable frequency of for example about 360 to about 800 Hz into a second frequency, by means of which the electrical loads24a,24b,24c,24dmay be operated.

An additional, second inverter18bis connected to a second generator12bvia the on-board network16. In the same way as the first inverter18a, the second inverter18bis configured to convert the first variable frequency of for example about 360 to about 800 Hz into a second frequency, by means of which the electrical loads24a,24b,24c,24dmay be operated.

The two inverters18a,18bmay each comprise a rectifier for rectifying the first frequency, a direct current link and a converter, which may convert the direct current from the direct current link into the second frequency. In one example, a rectifier which is configured to only produce low disturbances in the on-board network16, such as a 12-point rectifier, is generally very heavy, since it comprises a separate transformer. Owing to the fact that the electrical system22only comprises one inverter, or for reasons of redundancy only two inverters18a,18b, the electrical system22may be configured to be significantly lighter than an electrical system in which each of the electrical loads24a,24b,24c,24dwould have a separate inverter.

The two converters18a,18bmay be interconnected via a collector line26. The collector line may be a bus line or a bus bar, in which the electrical loads may be connected to the two inverters18a,18bvia a single line.

A first collector line switch28ais arranged in the collector line26and may disconnect the first inverter18afrom the collector line26. A second collector line switch28bis also arranged in the collector line26and may disconnect the second inverter18bfrom the collector line26. A third collector line switch28cis arranged in the collector line26in such a way that a first part30aof the collector line26may be disconnected from a second part30bof the collector line26.

The electrical loads24a,24b,24c,24dare each connected to the collector line26and may thus be connected to the two inverters18a,18b. In order for it to be possible to disconnect the electrical loads24a,24b,24c,24dindividually from the inverters18a,18band/or from the collector line26, each of the electrical loads24a,24b,24c,24dis associated with a load switch32a,32b,32c,32d.

The on-board network16and the collector line26may comprise three phases. The current in the on-board network16and in the collector line26may be three-phase current.

A first group34aof electrical loads24a,24bmay be connected in this case to the first part30aof the collector line26. A second group34bof electrical loads24c,24dmay be connected to the second part30bof the collector line26.

For example, the electrical loads24a,24b,24c,24dmay each comprise an electric motor36a,36b,36c,36dand a conveying device38a,38b,38c,38dwhich may be operated by means of the electric motor36a,36b,36c,36d. The conveying devices38a,38b,38c,38dmay be conveying devices for air or liquids which comprise fans or pumps, for example. In one example, a ventilation system or an air-conditioning system of the aircraft10may comprise a plurality of ventilation apparatuses24a,24b,24c,24dwhich serve to convey air from the surroundings into the inside of the aircraft10, to convey air between interior spaces of the aircraft10and/or to circulate air.

The aircraft10and in one example, the electrical system22may comprise a control unit40, for example a control for an air-conditioning system which may control the individual components18a,18b,28a,28b,28c,32a,32b,32c,32dof the electrical system via control lines22.

In one example, the control unit40may control the inverters18a,18band for example, the converters thereof in such a way (for example by means of pulse-width modulation) that the inverters18a,18bproduce a predetermined second frequency.

It is further possible for the control unit40to be able to open and close the load switches32a,32b,32c,32dselectively, i.e. separately, in order to disconnect the electrical loads24a,24b,24c,24dfrom the collector line26or the current supply thereof, or to connect said loads thereto. The load switches32a,32b,32c,32d(and the other switches28a,28b,28c) may for example be electrical relays.

It is also possible for the control unit40to open and close the collector line switches28a,28b, in order to disconnect the inverters18a,18bfrom the collector line26or to connect them thereto. The same applies to the collector line switch28c, in order to disconnect from one another or to interconnect the two parts30a,30bof the collector line26.

FIG. 3shows a flow diagram for a method for operating the electrical system by means of the control unit40. Normally, the two collector line switches28a,28bare closed and the collector line switch28cis open.

In block10, the control unit40determines a common conveying capacity for the conveying devices38a,38bof the first group34aof electrical loads24a,24b. For example, the conveying devices38a,38bare fans which blow air into the passenger cabin of the aircraft10.

In block12, the control unit40determines how the first group34aof electrical loads24a,24bmay be operated, in order to reach the previously determined conveying capacity. For this purpose, the control unit40may accordingly set the alternating current, which is produced by the inverter18a, with which the motors38a,38bfrom the first group34aare operated, and/or may determine the number of motors36a,36bwhich are to be operated with the alternating current in order to reach the desired conveying capacity.

In block14, the control unit40then opens and/or closes the load switches32a,32band operates the inverter18aaccordingly, in such a way that said inverter for example produces the second alternating current by means of pulse-width modulation and transforms the variable alternating current from the on-board network16having a variable first frequency into a second alternating current.

Blocks10to14may be accordingly carried out for the second group34bof electrical loads24c,24dand the inverter18b.

If one of the inverters18a,18bmalfunctions or fails, or for example one of the generators14a,14bdoes not provide sufficient electrical energy, one of the inverters18a,18bmay take over the function of the other.

For example, in the following the inverter18ahas failed. When this is determined by the control unit40, the control unit40disconnects the inverter18afrom the collector line26in block16by opening the switch28a. The first group34aof electrical loads is therefore disconnected from the inverter18a.

In block18, the control unit40closes the switch28aand thereby connects the first group34aof electrical loads to the second inverter18b.

In block20, the control unit40now operates the inverter18bin such a way that two groups34a,34bof electrical loads are operated by the inverter18b. For example, the inverter18bis configured to be redundant, in such a way that it may provide sufficient power for all the electrical loads. It is, however, also possible for the electrical loads to be operated at a reduced conveying capacity if an inverter18bis to supply both groups34a,34bwith electrical energy.