Classifications

• • H—ELECTRICITY
  • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
  • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
  • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
  • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
  • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
  • H02J9/062—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems for AC powered loads
• • H—ELECTRICITY
  • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
  • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
  • H02P9/00—Arrangements for controlling electric generators for the purpose of obtaining a desired output
  • H02P9/007—Control circuits for doubly fed generators
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D2221/00—Electric power distribution systems onboard aircraft
• • H—ELECTRICITY
  • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
  • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
  • H02J2310/00—The network for supplying or distributing electric power characterised by its spatial reach or by the load
  • H02J2310/40—The network being an on-board power network, i.e. within a vehicle
  • H02J2310/44—The network being an on-board power network, i.e. within a vehicle for aircrafts
• • H—ELECTRICITY
  • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
  • H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
  • H02P2101/00—Special adaptation of control arrangements for generators
  • H02P2101/30—Special adaptation of control arrangements for generators for aircraft

Definitions

• Power distribution device for distributing power and method for distributing power
• the present invention relates to a power distribution apparatus for distributing power and method for distributing power.
• AC grids are known at a constant grid frequency.
• variable frequency AC grids and, thirdly, DC grids are known.
• the first approach of the constant frequency AC mains described above has the particular advantage over variable frequency ones in that all those loads which are to be operated at the same voltage and speed during the flight of the aircraft can be connected directly to the power distribution network ,
• These consumers are for example fuel pumps, hydraulic pumps or fans.
• IDG integrated drive generators
• VFGs variable speed generators
• the DC voltage network is an alternative to the AC voltage networks.
• DC motors or DC generators with commutators should not be used in commercial aircraft, since these are very maintenance-prone and thus cost-intensive due to the required carbon brushes, brushless DC technology is used ,
• the generator or motor is operated with alternating voltage, which is generated by special motor control devices from a DC voltage network, for example, 270 V.
• the document US 4,357,524 shows an electric heating control device for heating control of an aircraft window. Furthermore, the document DE 198 21 952 C2 describes a power supply unit on board an aircraft.
• a power distribution apparatus for distributing power, in particular in an aircraft, comprising: a number N1 of conversion devices having a respective cascade generator for converting a first portion of a provided mechanical power into a first electrical power having an AC voltage a constant amplitude and constant frequency and having a respective frequency converter for providing a second electrical power having the constant amplitude, constant frequency alternating voltage in response to a second portion of the provided mechanical power; a number N2 of constant-frequency buses for respectively transmitting the constant-frequency electric power provided by the at least one converting means to a number N3 of consumers including at least a number N4 of consumers to be regulated in power consumption; and a number N4 of control devices, the respective control device being coupled between the respective load to be regulated and the constant frequency bus and is set up to regulate the power consumption of the consumer to be regulated.
• a method for distributing power comprising the following steps: a) providing a number N 1 of conversion devices with a respective cascade generator for converting a first part of a provided mechanical power into a first electrical power an AC voltage having a constant amplitude and at a constant frequency and having a respective frequency converter for providing a second electrical power with the AC voltage having the constant amplitude and the constant frequency in response to a second part of the provided mechanical power; b) providing a number N2 of constant frequency buses for respectively transmitting the constant frequency electrical power provided by the at least one conversion device to a number N3 of consumers including a number N4 of consumers to be regulated in power consumption; c) arranging a respective control device between the respective load to be controlled and the constant frequency bus; and d) controlling the power consumption of the controlled consumer ⁇ Chers by means of the control device is arranged.
• An advantage of the present invention is that the power distribution device according to the invention or the method according to the invention for distributing the power Advantages of a constant frequency network and combines the advantages of a generator without constant speed gearbox. Furthermore, it is possible according to the invention to couple a fuel cell as an additional energy source to the power distribution device according to the invention.
• Another advantage of the present invention is that, for the power distribution apparatus according to the invention, only a single type of network, namely a constant frequency mains alternating current network, is used for the power distribution and thus no transformations between power grids are required. This advantageously means significantly reduced energy losses in the power distribution network according to the invention or in the power distribution device according to the invention.
• the architecture of the power distribution device according to the invention results in greatly reduced power in relation to the total power provided, which would have to be conducted via converters. As a result, they can also be designed correspondingly smaller, which allows a further reduction in energy losses. This advantageously causes a minimization of the required effort for cooling measures, and ultimately also reduces the overall mass of the aircraft and thus the resulting costs.
• the power distribution device can also integrate one or more fuel cells in its network architecture, which make it possible to flexibly adjust the power provided to the individual buses to the power requirements of the connected consumers. This results in an improved utilization of existing power and increased redundancy.
• the use of a three-phase system, such as the constant frequency AC power grid of the present invention allows the provision of three different voltage systems as the only type of network without the need for dedicated conversion. It is thus a more efficient adaptation to the needs of the connected loads possible, as for example in a DC voltage network.
• the proposed architecture of the power distribution apparatus of the present invention can thus reduce the complexity of the network for powering the aircraft.
• a separate control device or regulating device is provided for each consumer to be regulated, which is dimensioned precisely for this. This results in a reduced development effort and a separate design of the individual control devices is possible.
• cascade generators are used, which on the in the publication Fräger, Carsten: “Novel cascade machine for brushless speed control drives with low power converter effort", Dusseldorf, VDI-Verlag, 1995, and on in US Pat. No. 7,045,925 B2 based on the generator concept and its generator-like applicability in Fräger, Carsten, "Cascade generator for wind power plants", drive and circuit technology,
• the advantage of this arrangement lies in the fact that the main power of the generator with the synchronous frequency of the generator, whose shaft is coupled to the engine of the aircraft, is fed directly into the network and only the differential power must be routed through the frequency converter. This allows it to be made considerably smaller, thus reducing the thermal losses and the mass.
• the engine, the generator and the intermediate transmission are preferably designed such that the generator is driven at synchronous speed when the engine rotates at cruising speed.
• the AC power supply of the invention is proposed with a constant frequency, since this is very suitable for the operation of consumers, such as motors or cascade motors, and also provides without a reversal three different voltage systems.
• These are preferably the full three-phase three-phase system, a single-phase AC system with the outer conductor voltage and a similar one with a factor of 1 / -J ⁇ smaller voltage.
• the voltage level for the buses can preferably be adjusted freely, but provides a mains voltage of 230/400 volts to achieve compared to conventional 115/200-volt networks smaller currents and thus a lower cable mass. This provides various voltage systems for using different voltages for each consumer.
• each consumer can be supplied with the most suitable voltage for this, whereby the overall system can be further optimized.
• the coupling of at least one low voltage DC voltage network with a preferred voltage of 28 volts is proposed, for example, to power the avionics and other electrical control and supervisory units.
• a power supply device is provided with a plurality of power supply units for respectively providing the constant frequency electrical power, wherein the respective power supply unit acts as a power supply unit N1 of the conversion means and / or one of a number N5 of fuel cells and / or one of a number N6 of terminals for coupling an external power source for providing a constant frequency electric power.
• a fuel cell basically supplies DC voltage, a conversion is required here in order to allow a feed into the intended AC power supply with a constant frequency.
• the fuel cell is preferably designed so that the delivered voltage can be converted by pure inversion into the selected mains voltage and no transformer is required.
• a controllable switching device is provided, which is set up for switching a respective power supply unit to a respective one of the number N2 of the constant frequency buses.
• the switching device or switching logic according to the invention it is possible to supply each of the existing buses from each of the sources of the power supply device.
• two engine generators should not feed the same bus at the same time or be connected to the external supply, as this synchronization of the actual voltage and phase would be required to prevent damage to the components.
• the present invention dispenses in this area with a coupling of the networks.
• both a bus may be supplied by a fuel cell stack alone and a fuel cell stack combined with one of the other sources.
• the inverter is preferably operated in the first case as a self-commutated inverter and in the second case, when combined with another source, as a foreign-guided inverter.
• the number N4 of consumers to be regulated with regard to their power consumption has a first quantity Ul of cascade motors to be controlled and a second quantity U2 of consumers to be regulated, which can be regulated within a range of 0% to 100% of their power consumption.
• the respective control device which is arranged coupled between the respective constant-frequency bus and the respective cascade motor, designed as a frequency converter.
• the respective control device which between the respective constant-frequency bus and a respective one of the second set U2 is arranged coupled to the load to be controlled, designed as a phase control.
• the number N3 of the consumers includes the number N4 of the consumers to be regulated with respect to their power consumption and a number N7 of unregulated consumers.
• Unregulated consumers which should only be switched on and off, can be connected directly to the respective bus.
• the connected motors as exemplary loads then rotate at a constant speed, as they are supplied directly by the constant frequency network. All other non-regulated or unregulated consumers are supplied with a constant voltage and constant frequency.
• the consumers to be regulated are regulated within different operating points. These then require a conversion by means of the corresponding control device, the structure of which depends on how large the required control range is. If the factor between minimum and maximum required speed of the motor is less than or equal to 2, then the above-described concept of the cascade motor is used.
• the power to be converted can be considerably reduced and the converter designed correspondingly small.
• a phase control is used, which allows a relatively effective conversion of the AC voltage of the bus in the voltage required in the respective control state.
• the number N2 of the constant frequency buses includes a first set M1 of main buses and a second set M2 of emergency buses.
• the controllable switching device switches the respective power supply unit to a respective one of the number N2 of the constant frequency buses as a function of a determined load distribution.
• the appropriate selection of the inverters for the fuel cell preferably allows both a bus to be powered by a single fuel cell stack and a fuel cell stack combined with another source.
• the inverter can be operated as a self-commutated inverter and in the second case when combined with another source as an externally controlled inverter.
• a number N5 of fuel cells is provided, wherein the respective fuel cell is coupled to the switching device by means of an inverter.
• the respective inverter is designed as a foreign-guided inverter.
• At least one transformer rectifier device is provided, which couples one of the number N2 of the constant frequency buses to a low-voltage DC voltage network.
• the number of transformer rectifier devices is equal to N2.
• At least one mechanical provisioning device is provided for providing the mechanical power, which preferably comprises an engine of the aircraft.
• Fig. 1 is a schematic block diagram of one embodiment of a power distribution apparatus for distributing power in an aircraft
• FIG. 2 is a schematic flow diagram of one embodiment of a method for distributing power in an aircraft.
• the power distribution device 1 has a number N 1 of conversion devices 2, a number N 2 of constant frequency buses 5, 6, and a number N 4 of control devices 13, 14.
• the conversion device 2 has a cascade generator 3 and a frequency converter 4 coupled to the cascade generator 3.
• the cascade generator 3 is designed for converting, in particular for direct conversion, of a first part of a mechanical power provided into a first electrical power II having an alternating voltage with a constant amplitude and at a constant frequency.
• the frequency converter 4 is for providing a second electric power 12 having the constant amplitude, constant frequency alternating voltage in response to a second part the provided mechanical power so that deviations of the rotational speed of the input shaft are compensated by the synchronous speed.
• the power 13 as the output power of the conversion device 2 according to FIG. 1 is the sum of the first electrical power Il and the second electric power 12.
• the respective constant-frequency bus 5, 6 is arranged to transmit the constant-frequency electrical power 13 provided by the at least one conversion device 2 to a number N3 of consumers 7-12, which has at least a number N4 of consumers to be regulated with regard to their power consumption 11, 12 includes.
• the respective control device 13, 14 is arranged coupled between the respective load to be controlled 11, 12 and the respective constant-frequency bus 5, 6.
• the regulating device 13, 14 is set up to regulate the power consumption of the consumer 11, 12 to be regulated.
• the power distribution device 1 preferably has a power supply device 15 with a plurality of power supply units 2, 16-19.
• the respective power supply unit 2, 16-19 is, for example, a conversion device 2, a fuel cell 16, 17 or a connection 18, 19 for coupling an external power source to provide a constant frequency electrical power.
• the power distribution device 1 preferably has a controllable switching device 20, which is set up for switching a respective power supply unit 2, 16-19 to a respective one of the number N2 of the constant frequency buses 5, 6.
• the controllable switching device 20 preferably switches as a function of a specific or determined load distribution within the network.
• the number N4 of the consumers 11, 12 to be regulated with respect to their power consumption has a first quantity Ul of cascade motors 11 to be regulated and a second quantity U2 of consumers 12 to be regulated, which are adjustable in a range from 0 to 100% of their power consumption are rules.
• the respective control device 14 which is arranged coupled between the respective constant-frequency bus 5, 6 and a respective one of the second set U2 of the load to be controlled 12, as a phase control 14 is formed.
• the number N3 of consumers 7-12 has the number N4 of consumers to be regulated in terms of their power consumption 11, 12 and a number N7 of unregulated consumers 7-10.
• the unregulated consumers 7-10 include, for example, a fuel pump or a hydraulic pump.
• the number N2 of the constant frequency buses 5, 6 comprises a first set M1 of main buses 5 and a second set M2 of emergency buses 6.
• the power distribution device 1 has a number N8 of fuel cells 16, 17, wherein the respective fuel cell 16, 17 by means of an inverter 21, 22 with the switching device 20 is coupled.
• the respective inverter 21, 22 is preferably designed as a foreign-guided inverter.
• the power distribution device 1 may preferably have a number of transformer rectifier devices 23-25, the respective transformer rectifier device 23-25 having one of the number N2 of the constant frequency buses 5, 6 with at least one low-voltage direct current voltage.
• Network 26 couples.
• the low-voltage direct-voltage network 26 preferably comprises DC voltage buses 27, batteries 29 and a corresponding consumer, such as the avionics 28.
• mechanical power for the power distribution device 1 is provided coupled from a number of engines of the aircraft.
• the coupling preferably takes place between one of the engines and at least one of the number N 1 of conversion units via a mechanical shaft.
• a number Nl of conversion devices 2 is provided.
• the respective conversion device 2 has a cascade generator 3 for converting a first part of a provided mechanical power into a first electrical one Power Il with a constant amplitude, constant frequency alternating voltage and with a respective frequency converter 4 for providing a second electrical power 12 with the constant amplitude and constant frequency alternating voltage in response to a second part of the provided mechanical power, such that Deviations of the speed of the input shaft from the synchronous speed can be compensated.
• the number N3 of consumers 7-12 comprises at least a number N4 of consumers 11, 12 to be regulated in terms of their power consumption.
• a controllable switching device 20 is provided, which is set up for switching a respective conversion device 2 to a respective constant-frequency bus 5, 6.
• a power supply device 15 is preferably provided with a plurality of power supply units 2, 16-19 for respectively providing the constant-frequency electrical power 13, the respective power supply unit being provided as one of the number N1 of the conversion unit.
• Devices 2 and / or as one of a number N5 of fuel cells 16, 17 and / or as one of a number N6 of terminals 18, 19 for coupling an external power source for providing a constant-frequency electric power is formed.
• the controllable switching device or circuitry preferably for switching a respective examrgnas- unit 2, 16-19 set to a respective one of the number N2 of the constant frequency buses 5.6.
• a respective control device 13, 14 is arranged between the respective consumer to be controlled 11, 12 and the respective constant-frequency bus 5, 6.
• the power consumption of the consumer 11, 12 to be regulated is regulated by means of the arranged regulating device 13, 14.

Landscapes

• Engineering & Computer Science (AREA)
• Power Engineering (AREA)
• Business, Economics & Management (AREA)
• Emergency Management (AREA)
• Supply And Distribution Of Alternating Current (AREA)
• Control Of Eletrric Generators (AREA)

Applications Claiming Priority (3)

Publications (1)

Family

ID=42104771

Family Applications (1)

Country Status (9)

Families Citing this family (14)

Family Cites Families (16)

• 2008
  • 2008-11-10 DE DE102008043626A patent/DE102008043626A1/de not_active Withdrawn
• 2009
  • 2009-11-10 WO PCT/EP2009/064915 patent/WO2010052338A1/de active Application Filing
  • 2009-11-10 JP JP2011535136A patent/JP2012508553A/ja active Pending
  • 2009-11-10 US US13/127,857 patent/US8928171B2/en active Active
  • 2009-11-10 RU RU2011117087/07A patent/RU2011117087A/ru not_active Application Discontinuation
  • 2009-11-10 CN CN200980144898.7A patent/CN102210094B/zh active Active
  • 2009-11-10 BR BRPI0921532A patent/BRPI0921532A2/pt not_active Application Discontinuation
  • 2009-11-10 CA CA2741815A patent/CA2741815A1/en not_active Abandoned
  • 2009-11-10 EP EP09760793A patent/EP2345149A1/de not_active Withdrawn

Non-Patent Citations (1)

Also Published As

Similar Documents

Legal Events